CN108194294B - Coaxial-type anodized insulation type pulsed plasma thruster - Google Patents
Coaxial-type anodized insulation type pulsed plasma thruster Download PDFInfo
- Publication number
- CN108194294B CN108194294B CN201711398769.3A CN201711398769A CN108194294B CN 108194294 B CN108194294 B CN 108194294B CN 201711398769 A CN201711398769 A CN 201711398769A CN 108194294 B CN108194294 B CN 108194294B
- Authority
- CN
- China
- Prior art keywords
- anode
- cathode
- plasma
- insulating cylinder
- type
- 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.)
- Active
Links
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
- F03H1/0087—Electro-dynamic thrusters, e.g. pulsed plasma thrusters
Abstract
The invention discloses a kind of coaxial-type anodized insulation type pulse plasma propellers, it is related to microsatellite propeller technical field, including cathode, anode and it is arranged insulating cylinder on the cathode, cathode is cylindric, the front end of cathode is equipped with discharge end, anode is the cylinder-like structure being fixed on insulation drum outer wall, and the inner wall of anode is in contact with the outer wall of insulating cylinder；Anode outer surface is enclosed with insulating layer；The axis of cathode, anode and insulating cylinder coincides；The cylindrical end of cathode is electrically connected external circuit negative high voltage terminal, the plus earth.The present invention is wrapped up anode by insulating cylinder and insulating layer, to block channel of the plasma to anode movement, is sprayed more plasmas axially along insulating cylinder, is improved the density of plasma jet.Plasma is ejected axially under the effect of hump current potential along insulating cylinder by the way that insulating cylinder is arranged, and forms the plasma jet that energy is high, directionality is good.
Description
Technical field
The present invention relates to microsatellite propeller technical fields, and in particular to a kind of coaxial-type anodized insulation type pulse etc. from
Sub- propeller.
Background technique
High-energy, highdensity ion metal plasma can be generated in vacuum gap electric discharge.The plasma of generation can
To be applied to ion implantation technique, change the surface nature of material；It can also be applied to pulsed plasma thruster, defended to be small
Star pose adjustment provides power.
In vacuum gap electric discharge, electronics collides under field emission effect with the metallic vapour from cathode point
Ionization generates metal ion and electronics.Then, electronics is to anode movement, and metal ion can be assembled near cathode, thus
A positive higher space potential (hump current potential) is formed near cathode.Under the action of hump current potential, metal ion is led
Draw electronics to all the winds to move.
Traditional vacuum gap discharge plasma generating mode uses bare metal discharge electrode structure, but generates big
Part plasma enters metal electrode under the action of external electric field, forms circuital current, only small part plasma from
Electrode ejects.Therefore, using the plasma propeller of bare metal electrode structure, that there are thrusts is insufficient, stability is poor, imitates
The low problem of rate.
Document " work of Liu Wenzheng, Chen Xiuyang, Cui Weisheng, Dou Zhijun cone-screw electrode in vacuum plasma generation
With [J] high-voltage technology, 2017, a kind of cone-screw electrode structure is proposed in 06:1863-1867. ", which utilizes spiral shell
It revolves shape anode and generates the generation constraint of axial magnetic field plasma.It compared to simultaneous quantitative cone-tubular electrode and cone-helical form
The plasma density that electrode generates, it was demonstrated that cone screw electrode can improve the plasma density generated and fixed using magnetic field
Tropism.But only the theory of plasma can effectively be fettered to the document by proposing and demonstrate helical anode structure, not
Fundamentally effectively block plasma motion to the channel of electrode.
Summary of the invention
The purpose of the present invention is to provide a kind of coaxial-types that can be improved plasma jet density and jet orientation
Anodized insulation type pulsed plasma thruster, to solve conventional plasma propeller plasma present in above-mentioned background technique
The technical problem that body jet density is not high, thrust is insufficient.
To achieve the goals above, this invention takes following technical solutions:
A kind of coaxial-type anodized insulation type pulse plasma propeller, including cathode and anode, the cathode be it is cylindric,
The front end of the cathode is equipped with discharge end, and insulating cylinder is arranged on the cathode, and the anode is fixed on the outer of the insulating cylinder
On wall；The anode is coated with insulating layer；The axis of the cathode, the anode and the insulating cylinder coincides.
Preferably, the shape of the discharge end is one of circular cone figure, evagination camber, indent camber or boss type.
Preferably, the anode is set as cylinder type.
Preferably, the anode is set as helical ring.
Preferably, the cathode is made of magnetic conductive metal material.
Preferably, the insulating cylinder is made of ceramic materials.
Preferably, the insulating layer is made of teflon material.
Preferably, the length of the anode is not less than 1mm.
Preferably, the top of the discharge end is located in the length range of the anode.
Preferably, the negative high voltage terminal of the cathode electrical connection discharge circuit, the plus earth.
The invention has the advantages that: the radial motion of plasma is blocked by the way that insulating cylinder is arranged, in the blocking of insulating cylinder
And under constraint effect, to form a higher hump current potential near cathode, plasma is under the effect of higher current potential
It is ejected along insulating cylinder, forms energy height, the better plasma jet of directionality；By insulating cylinder and insulating layer by anode
Package enables more plasmas axially to spray along insulating cylinder to block channel of the plasma to anode movement,
The density of plasma jet is improved, to provide stable, reliable thrust for propeller.
The additional aspect of the present invention and advantage will be set forth in part in the description, these will become from the following description
Obviously, or practice through the invention is recognized.
Detailed description of the invention
In order to illustrate the technical solution of the embodiments of the present invention more clearly, required use in being described below to embodiment
Attached drawing be briefly described, it should be apparent that, drawings in the following description are only some embodiments of the invention, for this
For the those of ordinary skill of field, without creative efforts, it can also be obtained according to these attached drawings others
Attached drawing.
Fig. 1 is coaxial-type anodized insulation type pulsed plasma thruster structure chart described in the embodiment of the present invention.
Fig. 2 is coaxial-type anodized insulation type pulsed plasma thruster electrode discharge circuit described in the embodiment of the present invention
Figure.
Fig. 3 is the plasma density distribution feelings generated with nonisulated anode and insulation anode that the embodiment of the present invention measures
Condition figure.
Fig. 4 is the straight of the insulating cylinder of coaxial-type anodized insulation type pulsed plasma thruster described in the embodiment of the present invention
Space electric field cloud charts when diameter is 4mm.
Fig. 5 is the straight of the insulating cylinder of coaxial-type anodized insulation type pulsed plasma thruster described in the embodiment of the present invention
Space electric field cloud charts when diameter is 1mm.
Fig. 6 is that the insulating cylinder of coaxial-type anodized insulation type pulsed plasma thruster described in the embodiment of the present invention stretches out
Space electric field vector distribution map when the different length of insulating layer right side.
Wherein: 1- cathode；2- anode；3- insulating cylinder；4- discharge end；5- insulating layer.
Specific embodiment
Embodiments of the present invention are described in detail below, and the example of the embodiment is shown in the accompanying drawings, wherein from beginning
Same or similar element or element with the same or similar functions are indicated to same or similar label eventually.Below by attached
The embodiment of figure description is exemplary, and for explaining only the invention, and is not construed as limiting the claims.
Those skilled in the art of the present technique are appreciated that unless expressly stated, singular " one " used herein, " one
It is a ", " described " and "the" may also comprise plural form.It is to be further understood that being arranged used in specification of the invention
Diction " comprising " refer to that there are the feature, integer, step, operation, element and/or component, but it is not excluded that in the presence of or addition
Other one or more features, integer, step, operation, element and/or their group.It should be understood that " connection " used herein
Or " coupling " may include being wirelessly connected or coupling, the wording "and/or" used include one or more associated list
Any cell of item and all combination.
Those skilled in the art of the present technique are appreciated that unless otherwise defined, all terms used herein (including technology art
Language and scientific term) there is meaning identical with the general understanding of those of ordinary skill in fields of the present invention.Should also
Understand, those terms such as defined in the general dictionary, which should be understood that, to be had and the meaning in the context of the prior art
The consistent meaning of justice, and unless defined as here, it will not be explained in an idealized or overly formal meaning.
It is of the invention for ease of understanding, explanation is further explained to the present invention with specific embodiment with reference to the accompanying drawing, and
Specific embodiment does not constitute the restriction to the embodiment of the present invention.
Fig. 1 is coaxial-type anodized insulation type pulsed plasma thruster structure chart described in the embodiment of the present invention, and Fig. 2 is
Coaxial-type anodized insulation type pulsed plasma thruster electrode discharge circuit diagram described in the embodiment of the present invention, Fig. 3 are this hair
The plasma density distribution situation map generated with nonisulated anode and insulation anode that bright embodiment measures, Fig. 4 are the present invention
The space electric field when diameter of the insulating cylinder of coaxial-type anodized insulation type pulsed plasma thruster described in embodiment is 4mm
Cloud charts, Fig. 5 are the insulating cylinder of coaxial-type anodized insulation type pulsed plasma thruster described in the embodiment of the present invention
Space electric field cloud charts when diameter is 1mm, Fig. 6 be coaxial-type anodized insulation type pulse etc. described in the embodiment of the present invention from
The insulating cylinder of daughter propeller stretches out the space electric field vector distribution map when different length of insulating layer right side.
It should be appreciated by those skilled in the art that attached drawing is the schematic diagram of embodiment, the component in attached drawing is not necessarily
Implement necessary to the present invention.
As shown in Figure 1, the embodiment of the invention provides a kind of coaxial-type anodized insulation type pulse plasma propellers, including
Cathode 1 and anode 2, the cathode 1 be it is cylindric, the front end of the cathode 1 is equipped with discharge end 4, is arranged on the cathode 1 absolutely
Edge cylinder 3, the anode 2 are fixed on the outer wall of the insulating cylinder 3, and the anode 2 is coated with insulating layer 5；The yin
The axis of pole 1, the anode 2 and the insulating cylinder 3 coincides.The anode 2 is cylindrical shape, and the anode 2 is set in described
On the outer wall of insulating cylinder 3, the inner wall of the anode 2 is in contact with the outer wall of the insulating cylinder 3.The setting of insulating cylinder 3 blocks
The movement that plasma is radially spread makes the discharge end 4 of cathode 1 nearby produce higher hump current potential, higher hump
Current potential plasma produces bigger thrust, thus keep the movement velocity of plasma and directionality higher, it is a large amount of to move
The axial jet that speed and the higher plasma of directionality are formed has higher energy.The setting of insulating layer 5 blocks
Movement of the gas ions to anode keeps the plasma being axially moved more, improves the density of plasma jet.
In practical applications, the anode 2 can also be set as helical ring, and solenoid is set on the outer wall of insulating cylinder 3, spiral shell
The anode of coiled type can generate stronger axial magnetic field in insulating cylinder, and axial magnetic field can effectively constrain plasma to radial direction
The movement in direction reduces the radial diffusion of plasma, increases plasma density and energy that electrode ejects.
In one particular embodiment of the present invention, the shape of the discharge end 4 is circular cone figure, evagination camber, indent
One of camber or boss type.
In practical applications, the shape of discharge end 4 is not limited by above-mentioned shape, its any end has protrusion, and
The structure of vacuum discharge can be generated as discharge end, all within the scope of the present invention using protrusion.
In one particular embodiment of the present invention, the cathode 1 is made of magnetic conductive metal material.
In one particular embodiment of the present invention, the insulating cylinder 3 is made of insulating material, preferred that ceramics can be used
Material.
In practical applications, the effect of above-mentioned insulating cylinder 3 is the radial motion of barrier plasma, and material, which can be used, appoints
What material with insulation effect is made, and is not limited by above-mentioned ceramic material, as long as capableing of the radial direction of barrier plasma
Movement.
In one particular embodiment of the present invention, the insulating layer 5 is made of teflon material.
In practical applications, the effect of above-mentioned insulating layer 5 is movement of the barrier plasma to anode, to guarantee to insulate
Cylinder 3 in have the plasma being more axially moved, any material with insulation effect can be used in making material, not by
The limitation of above-mentioned teflon material, preferably teflon material are to utilize its non-stick, heat resistance, sliding property, moisture resistance, wear-resistant
The excellent physicochemical stabilities such as property, corrosion resistance, to guarantee the performance of plasma thrusters.
In one particular embodiment of the present invention, the cathode 1 is electrically connected the negative high voltage terminal of discharge circuit, the sun
Pole 2 is grounded.
The principle of the present invention is as follows:
In vacuum gap electric discharge, electronics collides under field emission effect with the metallic vapour from cathode point
Ionization generates metal ion and electronics.Then, electronics is to anode movement, and metal ion can be assembled near cathode, thus
A positive higher space potential (hump current potential) is formed near cathode.Under the action of hump current potential, metal ion is led
Draw electronics to all the winds to move.And it is based on electrode structure proposed by the present invention, after the anodized insulation of electrode is wrapped up, hinder
Channel of the plasma motion to electrode, so that more plasmas are ejected along insulating sleeve.What cathode generated etc.
Gas ions are acted on by the blocking and constraint of insulating cylinder, can only be axially moved along insulating sleeve.Finally, in the work of hump current potential
It is axially ejected with lower along insulating cylinder, forms plasma jet.Therefore, in high vacuum environment, using in cathode and sun
Cone-cylinder electrode structure that the anodized insulation coated of insulating cylinder is increased between pole is capable of forming high density, orientation stablizes injection
Plasma jet.
It is as follows specifically to test process for the jet characteristics of plasma in the present invention:
During specific experiment, coaxial-type anodized insulation type pulse plasma propeller packet described in the embodiment of the present invention
Include cylinder type cathode 1, cone cell is made in the front end discharge end 4 of cathode 1, for fetter generation plasma 3 He of insulating cylinder
Wrap up the insulating layer 5 of anode 2.
Wherein, Anodic 2 is cylindrical shape, and cathode 1 is that coniform structure is made in one end, which is the electric discharge of cathode
End 4.But the tip of the cone of cone is not easy too sharp, otherwise point of discharge can be caused to deviate, influence discharge stability.Therefore, negative
The tip of the tapered end of pole 1 will keep certain circularity.For example, tapered end tip can be set to arcuation or spherical.
The bottom radius r of the discharge end 4 of cathode 1 and the range of cone height H ratio are 1:3 to 3:1, are specially r/ in this experiment
H=1:2.Cathode 1 is connected with the negative high voltage terminal of external circuit.The length of cylindrical anode 2 is not less than 1mm, of the invention
In test, the length of anode 2 can be specifically configured to 1mm.
The material of the columnar part of the metal cylinder of the cathode 1 uses the good permeance metal of irony.
The cylindrical anode 2 is connected to ground by plain conductor, and anode 2 and conducting wire all use wrapped with insulation.
In this experiment, cathode 1 uses lead metal, and that plays constraint action of plasma is set in the exhausted of 1 outer surface of cathode
The material of edge cylinder 3 is ceramics, and the material for playing the insulating layer 5 of package anode 2 is polytetrafluoroethylene (PTFE) (Teflon), anode 2
Material is metallic copper.
Discharge power supply in this experimentation uses pulsed discharge form, and specific discharge circuit is as shown in Figure 2.220V is handed over
Galvanic electricity source, boosts by transformer, charges after voltage doubling rectifing circuit transformation to capacitor C2.When to 3 gaps application firing pulses
When, 3 gap conductings constitute circuit through C2,27 Ω resistance, 160 μ H inductance and vacuum gap, and vacuum gap breakdown, which generates, puts
Electrical phenomena.Cathode connects power supply high-voltage end by binding post, and orificed anode passes through wired earth.
Fig. 3 is the density profile of the non-anodized insulation type electrode measured and the plasma of anodized insulation type electrode.By
For Fig. 3 it is found that compared with non-anodized insulation type electrode, the plasma density that anodized insulation type electrode generates is larger.Illustrate to utilize
Anodized insulation type electrode structure can obtain the metallic plasma of high density, vectored injection.
Test the test that the internal diameter plasma jet characteristics of 1, insulating cylinder 3 influence:
During discharge test, discharge test research, cathode have been carried out to the electrode structure of the insulating cylinder 3 of different-diameter
1 uses lead metal, cathode overall length 35mm, and the bottom radius r and height H ratio of conical end cathode are 1:2；The outer material of insulating cylinder 3 is
Ceramics, the length that the insulating cylinder 3 stretches out the right side insulating layer 5 of the anode 2 is 1mm；Play the insulation of package anode
The material of layer 5 is polytetrafluoroethylene (PTFE) (Teflon), anode lengths 1mm.Electrode and surrounding space field distribution are as shown in Figure 5.
It is as shown in table 1 that experiment measures the plasma generation Contrast on effect under the insulating cylinder 3 of different-diameter.
Plasma measurement result under 1 different insulative cylinder internal diameter of table
As shown in Table 1, in plasma jet channel, the plasma density phase that generates when 3 internal diameter of insulating cylinder is 1mm
Than the internal diameter in insulating cylinder 3 to increase 10.2% when 4mm, plasma spread speed is 4mm compared to the internal diameter of insulating cylinder 3
When spread speed increase 7.7%, jet length when plasma jet length compared to the internal diameter of insulating cylinder 3 is 4mm
Increase 57%.By the simulation result of Fig. 4, Fig. 5 it is found that the internal diameter of insulating cylinder 3 is smaller, cathode point electric field strength greatest around
It is bigger.Therefore, it discharges theoretical by vacuum gap it is found that reducing the internal diameter of insulating cylinder 3, interelectrode discharge voltage can be reduced.
According to analysis of experimental results it is found that the internal diameter of insulating cylinder 3 is smaller, the plasma radial move distance that cathode generates reduces,
The plasma generated is in the smaller interior barrier effect that just will receive insulating cylinder 3 of radial motion distance.Therefore, more gold
Belong to ion to be gathered near cathode 1, so that a higher hump current potential is formed near cathode 1, in the effect of hump current potential
Under, plasma jet finally obtains bigger spread speed.
The test that the length plasma jet characteristics of 5 right side of insulating layer influence is stretched out in experiment 2, insulating cylinder 3:
In this experiment, use aluminium as 1 material of cathode, insulating cylinder 3 internal diameter for 1mm, probed into edge cylinder 3 stretch out insulation
The length L plasma of 5 right side of layer generates the influence of effect, and it is as shown in table 2 that plasma generates effect.
Plasma measurement result under 2 different insulative tube length degree of table
Fig. 6 (a) is the insulating cylinder 3 of coaxial-type anodized insulation type pulsed plasma thruster described in the embodiment of the present invention
Space electric field vector distribution map when the length for stretching out 5 right side of insulating layer is 1mm, Fig. 6 (b) are described in the embodiment of the present invention
The insulating cylinder 3 of coaxial-type anodized insulation type pulsed plasma thruster stretches out the sky when length of 5 right side of insulating layer is 4mm
Between electric field intensity distribution map, Fig. 6 (c) be the embodiment of the present invention described in coaxial-type anodized insulation type pulsed plasma thruster
Insulating cylinder 3 stretch out 5 right side of insulating layer length be 7mm when space electric field vector distribution map.
As shown in Figure 6, on the one hand, insulating cylinder 3 is longer, and the electric field strength in cylinder is bigger, and the plasma acceleration time is longer,
Speed is bigger；From the analysis of experimental results of table 2: insulating cylinder 3 is longer, and the plasma more generated will be bound in insulating cylinder
In 3, being gathered in cathode 1, nearby metal ion density is improved, to form a higher hump current potential near cathode 1.Cause
This, increases the extension elongation of insulating cylinder 3, the jet stream performance of plasma can be improved, to improve pulsed plasma propulsion
Device efficiency.
Test the test that the material plasma jet characteristics of 3, discharge end 4 influence:
In vacuum gap electric discharge, the jet characteristics of the characteristic plasma of the material of 1 discharge end 4 of cathode have important shadow
It rings.3 internal diameter of insulating cylinder is being used under the electrode structure of 1mm, further to the electric discharge of the discharge end 4 made of copper, aluminium respectively
Characteristic is analyzed and researched.
Plasma jet measurement result under the different cathode materials of table 3
By 3 measurement result of table and analysis it is found that the work function of metallic lead is minimum, under identical structural parameters, lead material cathode
Discharge voltage is minimum, copper product cathodic discharge voltage highest.
Under respective firing potential, the electric field strength near copper electrode cathode tapered end is maximum, the plasma of generation
Density is also maximum.
In plasma communication process, there are Al2+, Al3+ in the plasma that wherein aluminum material cathodic discharge generates
Ion, the positive potential formed near cathode are higher [16].By hump theory it is found that the plasma that aluminum material cathode generates passes
It is bigger to broadcast speed, jet length is longer.
In conclusion the 2 coated electrode structure of insulated type anode with insulating cylinder 3 of the invention, insulating cylinder 3 hinder
The radial diffusion of plasma, the insulating layer 5 being wrapped in outside anode 2 prevent plasma to enter anode 2.It is insulated by setting
Cylinder 3 ejects plasma axially under the effect of higher hump current potential along insulating cylinder 3, forms energy height, directionality more
Good plasma jet；Anode 2 is wrapped up by insulating cylinder 3 and insulating layer 5, to block plasma to anode movement
Channel, make more plasmas along insulating cylinder axially spray, improve the density of plasma jet
Constraint ability to metal ion near cathode 1 can be improved using thinner insulating cylinder 3, thus close in cathode 1
Side forms higher positive space current potential.Increase the length that insulating cylinder 3 stretches out 5 right side of insulating layer, can be improved inside insulating cylinder 3
Axial electric field strength increases the plasma acceleration time.Therefore, using elongated insulating cylinder 3 can be improved metal ion etc. from
The jet stream performance of daughter.
Those of ordinary skill in the art will appreciate that: the component in device in the embodiment of the present invention can be according to embodiment
Description be distributed in the device of embodiment, corresponding change can also be carried out and be located at one or more dresses different from the present embodiment
In setting.The component of above-described embodiment can be merged into a component, can also be further split into multiple subassemblies.
The foregoing is only a preferred embodiment of the present invention, but scope of protection of the present invention is not limited thereto,
In the technical scope disclosed by the present invention, any changes or substitutions that can be easily thought of by anyone skilled in the art,
It should be covered by the protection scope of the present invention.Therefore, protection scope of the present invention should be with scope of protection of the claims
Subject to.
Claims (7)
1. a kind of coaxial-type anodized insulation type pulse plasma propeller, including cathode (1) and anode (2), the cathode (1) are
Cylindric, the front end of the cathode (1) is equipped with discharge end (4), it is characterised in that: is arranged with insulating cylinder on the cathode (1)
(3), the anode (2) is fixed on the outer wall of the insulating cylinder (3)；The anode (2) is coated with insulating layer (5)；
The axis of the cathode (1), the anode (2) and the insulating cylinder (3) coincides；The anode (2) is cylinder type or helical
The top of ring, the discharge end (4) is located in the length range of the anode (2), and institute is stretched out in the end of the insulating cylinder (3)
State the end face of insulating layer (5) far from cathode (1).
2. coaxial-type anodized insulation type pulse plasma propeller according to claim 1, it is characterised in that: the electric discharge
The shape for holding (4) is one of circular cone figure, evagination camber, indent camber or boss type.
3. coaxial-type anodized insulation type pulse plasma propeller according to claim 1, it is characterised in that: the cathode
(1) it is made of magnetic conductive metal material.
4. coaxial-type anodized insulation type pulse plasma propeller according to claim 1, it is characterised in that: the insulation
Cylinder (3) is made of ceramic materials.
5. coaxial-type anodized insulation type pulse plasma propeller according to claim 1, it is characterised in that: the insulation
Layer (5) is made of teflon material.
6. coaxial-type anodized insulation type pulse plasma propeller according to claim 1, it is characterised in that: the anode
(2) length is not less than 1mm.
7. coaxial-type anodized insulation type pulse plasma propeller according to claim 1-6, it is characterised in that:
The negative high voltage terminal of cathode (1) the electrical connection discharge circuit, anode (2) ground connection.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711398769.3A CN108194294B (en) | 2017-12-22 | 2017-12-22 | Coaxial-type anodized insulation type pulsed plasma thruster |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711398769.3A CN108194294B (en) | 2017-12-22 | 2017-12-22 | Coaxial-type anodized insulation type pulsed plasma thruster |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108194294A CN108194294A (en) | 2018-06-22 |
| CN108194294B true CN108194294B (en) | 2019-07-26 |
Family
ID=62583585
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711398769.3A Active CN108194294B (en) | 2017-12-22 | 2017-12-22 | Coaxial-type anodized insulation type pulsed plasma thruster |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108194294B (en) |
Families Citing this family (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109538431B (en) * | 2018-10-12 | 2020-09-08 | 北京交通大学 | Vacuum arc propeller based on multi-anode structure |
| CN109441747B (en) * | 2018-11-02 | 2020-08-14 | 北京航空航天大学 | Ignition mode of electric propulsion engine |
| CN109737023B (en) * | 2018-12-10 | 2021-02-19 | 兰州空间技术物理研究所 | Self-breakdown type pulse plasma thruster of annular cone structure anode |
| CN109751212B (en) * | 2019-01-28 | 2020-06-09 | 北京交通大学 | Pulse plasma propeller with micropore insulation anode |
| CN110012584B (en) * | 2019-03-22 | 2020-06-09 | 北京交通大学 | Pulse vacuum arc plasma thruster with segmented micropore insulation anode |
| CN112423460B (en) * | 2019-08-20 | 2023-03-21 | 新奥科技发展有限公司 | Plasma generator |
| CN111472954B (en) * | 2020-03-25 | 2021-10-01 | 北京交通大学 | Insulating anode cathode arc propeller with auxiliary suspension potential electrode |
| CN111654967B (en) * | 2020-06-09 | 2021-05-07 | 北京交通大学 | Double-jet pulse metal ion plasma propeller |
| CN111863566A (en) * | 2020-06-11 | 2020-10-30 | 北京交通大学 | Multi-electrode vacuum arc ion source |
| CN113357109B (en) * | 2021-06-30 | 2022-07-15 | 哈尔滨工业大学 | Ignition device of radio frequency ion thruster |
| CN114001003A (en) * | 2021-10-26 | 2022-02-01 | 北京理工大学 | Double-section coaxial toothed cathode pulse plasma thruster |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1158003C (en) * | 2001-10-25 | 2004-07-14 | 华中科技大学 | Capillary plasma generator |
| CN105704903B (en) * | 2016-03-16 | 2019-03-05 | 北京交通大学 | A kind of discharge electrode structure that the vacuum plasma based on magnetic fields generates |
-
2017
- 2017-12-22 CN CN201711398769.3A patent/CN108194294B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN108194294A (en) | 2018-06-22 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108194294B (en) | Coaxial-type anodized insulation type pulsed plasma thruster | |
| CN105704903B (en) | A kind of discharge electrode structure that the vacuum plasma based on magnetic fields generates | |
| US6737640B2 (en) | Electrospray ionization mass analysis apparatus and method thereof | |
| KR101620009B1 (en) | Plasma reactor having multiple attribute | |
| CA2968233C (en) | Mass spectrometer comprising a radio frequency ion guide having continuous electrodes | |
| JP2023051903A (en) | Energy-efficient plasma processes of generating free charges, ozone, and light | |
| US6455846B1 (en) | Sample inlet tube for ion source | |
| CN109538431A (en) | A kind of Vacuum Arc propeller based on multianode structure | |
| CN207458884U (en) | A kind of Plasma-cathode e-gun | |
| Liu et al. | Impact of the electric field distribution on the generation characteristics of vacuum-arc discharge plasmas | |
| CN109578233B (en) | Ablation type pulse plasma propeller based on multi-anode electrode structure | |
| CN105097413B (en) | Novel ion source and ionization method | |
| CN111863566A (en) | Multi-electrode vacuum arc ion source | |
| Li et al. | Effects of atmospheric-pressure discharge type on ionic wind velocity for needle-to-cylinder electrode | |
| CN110012584A (en) | Pulse Vacuum arc plasma propeller with segmentation microporous insulation anode | |
| CN107507749B (en) | Plasma cathode electron gun | |
| RU2185704C1 (en) | Spiral explosive magnetic generator | |
| RU2185705C1 (en) | Spiral explosive magnetic generator | |
| CN104412470A (en) | Spark gap with a capacitive energy accumulator | |
| CN109751212A (en) | Pulse plasma propeller with microporous insulation anode | |
| CN111654967B (en) | Double-jet pulse metal ion plasma propeller | |
| WO2022234039A1 (en) | Plasma reactor for plasma-based gas conversion comprising an effusion nozzle | |
| CN2709419Y (en) | Ozone generator | |
| CN107633986B (en) | Method for generating electron beam | |
| RU2114520C1 (en) | Pulse-operated plasma plant |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |