CN108194294A - Coaxial-type anodized insulation type pulsed plasma thruster - Google Patents
Coaxial-type anodized insulation type pulsed plasma thruster Download PDFInfo
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- CN108194294A CN108194294A CN201711398769.3A CN201711398769A CN108194294A CN 108194294 A CN108194294 A CN 108194294A CN 201711398769 A CN201711398769 A CN 201711398769A CN 108194294 A CN108194294 A CN 108194294A
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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
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 electrical connection external circuit negative high voltage terminal of cathode, the plus earth.The present invention is wrapped up anode by insulating cylinder and insulating layer, so as to block channel of the plasma to anode movement, more plasmas is made axially to be sprayed along insulating cylinder, improve the density of plasma jet.By setting insulating cylinder that plasma is made axially to be ejected along insulating cylinder under the effect of hump current potentials, the plasma jet that energy is high, directionality is good is formed.
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 technology
Vacuum gap electric discharge can generate high-energy, highdensity ion metal plasma.The plasma of generation can
To be applied to ion implantation technique, change the surface nature of material；Pulsed plasma thruster is can also be applied to, is 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, so as to
A positive higher space potential (hump current potentials) is formed near cathode.Under the action of hump current potentials, 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, there are thrust is insufficient, stability is poor, effect
The problem of rate is low.
Document " work of Liu Wenzheng, Chen Xiuyang, Cui Weisheng, Dou Zhi army cones-screw electrode in vacuum plasma generation
With [J] high-voltage technologies, 2017,06:A kind of cone-screw electrode structure is proposed in 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 utilize magnetic field to improve the plasma density of generation and fixed
Tropism.But only the theory of plasma can effectively be fettered to the document by proposing and demonstrate helical anode structure, not
Plasma motion is fundamentally effectively blocked to the channel of electrode.
Invention content
The purpose of the present invention is to provide a kind of coaxial-types that can improve plasma jet density and jet orientation
Anodized insulation type pulsed plasma thruster, to solve conventional plasma propeller plasma present in above-mentioned background technology
The technical issues of body jet density is not high, thrust is insufficient.
To achieve these goals, this invention takes following technical solutions：
A kind of coaxial-type anodized insulation type pulse plasma propeller, including cathode and anode, the cathode to be 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 kind in circular cone build, 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.
Advantageous effect of the present invention：By the way that insulating cylinder is set to block the radial motion of plasma, in the blocking of insulating cylinder
And under constraint effect, so as 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 so as to block channel of the plasma to anode movement, enables more plasmas axially to be sprayed along insulating cylinder,
The density of plasma jet is improved, so as 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
It obtains significantly or is recognized by the practice of the present invention.
Description of the drawings
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, the accompanying drawings in the following description is only some embodiments of the present invention, for this
For the those of ordinary skill of field, without creative efforts, others are can also be obtained according to these attached drawings
Attached drawing.
Fig. 1 is the coaxial-type anodized insulation type pulsed plasma thruster structure chart described in the embodiment of the present invention.
Fig. 2 is the 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 the 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 the 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 the coaxial-type anodized insulation type pulsed plasma thruster described in the embodiment of the present invention stretches out
Space electric field vector distribution map during the different length of insulating layer right side.
Wherein：1- cathodes；2- anodes；3- insulating cylinders；4- discharge ends；5- insulating layers.
Specific embodiment
Embodiments of the present invention are described in detail below, and the example of the embodiment is shown in the drawings, wherein from beginning
Same or similar element is represented to same or similar label eventually or there is the element of same or like function.Below by attached
The embodiment of figure description is exemplary, and is only used for explaining the present invention, and is not construed as limiting the claims.
Those skilled in the art of the present technique are appreciated that unless expressly stated, singulative " one " used herein, " one
It is a ", " described " and "the" may also comprise plural form.It is to be further understood that is used in the specification of the present invention arranges
Diction " comprising " refers to there are the feature, integer, step, operation, element and/or component, but it is not excluded that presence 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 " can include wireless connection or coupling, the wording "and/or" used includes 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 are (including technology art
Language and scientific terminology) there is the meaning identical with the general understanding of the 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, will not be with idealizing or the meaning of too formal be explained.
It is of the invention for ease of understanding, explanation is further explained the present invention with specific embodiment below in conjunction with the accompanying drawings, and
Specific embodiment does not form the restriction to the embodiment of the present invention.
Fig. 1 is the 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
Space electric field during a diameter of 4mm of the insulating cylinder of the coaxial-type anodized insulation type pulsed plasma thruster described in embodiment
Cloud charts, Fig. 5 are the insulating cylinder of the coaxial-type anodized insulation type pulsed plasma thruster described in the embodiment of the present invention
Space electric field cloud charts during a diameter of 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 during 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
Necessary to the implementation present invention.
As shown in Figure 1, an embodiment of the present invention provides a kind of coaxial-type anodized insulation type pulse plasma propeller, including
Cathode 1 and anode 2, the cathode 1 are cylindric, and 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；Described the moon
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 potentials, higher hump
Current potential plasma produces the thrust of bigger, a large amount of to move so as to make the movement velocity of plasma and directionality higher
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, the plasma for making axial movement is 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 radially
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 build, evagination camber, indent
One kind in camber or boss type.
In practical applications, the shape of discharge end 4 is not limited by above-mentioned shape, its any end carries protrusion, and
The structure of vacuum discharge can be generated as discharge end by the use of protrusion, all within the scope of the present invention.
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 materials, 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
The material what has insulation effect is made, and is not limited by above-mentioned ceramic material, as long as being capable 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, so as to ensure 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, moisture resistance, wear-resistant
The excellent physicochemical stabilities such as property, corrosion resistance, to ensure 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, so as to
A positive higher space potential (hump current potentials) is formed near cathode.Under the action of hump current potentials, metal ion is led
Draw electronics to all the winds to move.And 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.Cathode generation 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 potentials
It is axially ejected along insulating cylinder with lower, forms plasma jet.Therefore, in high vacuum environment, using in cathode and sun
Cone-cylinder electrode structure of the anodized insulation coated of insulating cylinder is increased between pole, high density can be formed, 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, the coaxial-type anodized insulation type pulse plasma propeller packet described in the embodiment of the present invention
Cylinder type cathode 1 is included, taper is made in the front end discharge end 4 of cathode 1, for fettering 3 He of insulating cylinder of the plasma of generation
Wrap up the insulating layer 5 of anode 2.
Wherein, Anodic 2 is cylindrical shape, and coniform structure is made for one end in cathode 1, 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, it is cloudy
The tip of the tapered end of pole 1 will keep certain circularity.For example, tapered end tip can be set as to arcuation or spherical.
The bottom radius r and cone height H of the discharge end 4 of cathode 1 than ranging from 1:3 to 3:1, it is 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, the present invention's
In experiment, 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 capacitance C2.When to 3 gaps application firing pulses
When, 3 gap conductings form 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-pressure side 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 of anodized insulation type electrode generation is larger.Illustrate to utilize
Anodized insulation type electrode structure can obtain high density, vectored injection metallic plasma.
Experiment 1, the test of the internal diameter plasma jet characteristics influence of insulating cylinder 3：
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, and cathode overall length 35mm, bottom radius r and the height H ratios 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 are 1mm；Play the insulation of package anode
The material of layer 5 is polytetrafluoroethylene (PTFE) (Teflon), anode lengths 1mm.Electrode and the distribution of surrounding space electric field are as shown in Figure 5.
It is as shown in table 1 that 3 time plasmas of insulating cylinder that experiment is measured in different-diameter generate Contrast on effect.
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% during 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 of cathode generation reduces,
The plasma generated will be by the barrier effect of insulating cylinder 3 in smaller radial motion distance.Therefore, more gold
Belong to ion to be gathered near cathode 1, so as to form a higher hump current potential near cathode 1, in the effect of hump current potentials
Under, plasma jet finally obtains the spread speed of bigger.
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 influence of the length L plasmas generation effect of 5 right side of layer, plasma generation effect are as shown in table 2.
Plasma measurement result under 2 different insulative tube length degree of table
Fig. 6 (a) is the insulating cylinder 3 of the 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) is described in the embodiment of the present invention
The sky when length that the insulating cylinder 3 of coaxial-type anodized insulation type pulsed plasma thruster stretches out 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 space electric field vector distribution map when the length of insulating layer 5 right side is 7mm.
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 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 improves, so as to form a higher hump current potential near cathode 1.Cause
This, increases the extension elongation of insulating cylinder 3, can improve the jet stream performance of plasma, is promoted so as to improve pulsed plasma
Device efficiency.
Experiment 3, the test of the material plasma jet characteristics influence of discharge end 4：
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.In the case where using electrode structure of 3 internal diameter of insulating cylinder for 1mm, further to respectively made of copper, aluminium discharge end 4 electric discharge
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, wherein there are Al2+, Al3+ in the plasma of aluminum material cathodic discharge generation
Ion, the positive potential higher [16] formed near cathode.By hump theories it is found that the plasma of aluminum material cathode generation passes
Speed bigger is broadcast, jet length is longer.
In conclusion the 2 coated electrode structure of insulated type anode with insulating cylinder 3 of the present 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 makes plasma be ejected under the effect of higher hump current potentials along insulating cylinder 3 is axial, forms energy height, directionality more
Good plasma jet；Anode 2 is wrapped up by insulating cylinder 3 and insulating layer 5, so as to block plasma to anode movement
Channel, more plasmas is made axially to be sprayed along insulating cylinder, improve the density of plasma jet
Constraint ability to metal ion near cathode 1 can be improved using thinner insulating cylinder 3, so as near 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 improve inside insulating cylinder 3
Axial electric field strength increases the plasma acceleration time.Therefore, using elongated insulating cylinder 3 can improve metal ion etc. from
The jet stream performance of daughter.
One 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, respective change can also be carried out and be located at one or more dresses different from the present embodiment
In putting.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 protection scope of the present invention be not limited thereto,
Any one skilled in the art in the technical scope disclosed by the present invention, the change or replacement that can be readily occurred in,
It should be covered by the protection scope of the present invention.Therefore, protection scope of the present invention should be with scope of the claims
Subject to.
Claims (10)
1. a kind of coaxial-type anodized insulation type pulse plasma propeller, including cathode (1) and anode (2), the cathode (1) is
Cylindric, the front end of the cathode (1) is equipped with discharge end (4), it is characterised in that：Insulating cylinder is arranged 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.
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 kind in circular cone build, 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 anode
(2) it is cylinder type.
4. coaxial-type anodized insulation type pulse plasma propeller according to claim 1, it is characterised in that：The anode
(2) it is helical ring.
5. 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.
6. 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.
7. coaxial-type anodized insulation type pulse plasma propeller according to claim 3, it is characterised in that：The insulation
Layer (5) is made of teflon material.
8. coaxial-type anodized insulation type pulse plasma propeller according to claim 3, it is characterised in that：The anode
(2) length is not less than 1mm.
9. coaxial-type anodized insulation type pulse plasma propeller according to claim 8, it is characterised in that：The electric discharge
The top at end (4) is located in the length range of the anode (2).
10. according to claim 1-9 any one of them coaxial-type anodized insulation type pulse plasma propellers, feature exists
In：The negative high voltage terminal of cathode (1) the electrical connection discharge circuit, anode (2) ground connection.
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| CN109441747A (en) * | 2018-11-02 | 2019-03-08 | 北京航空航天大学 | A kind of electric propulsion engine sparking mode |
| CN109538431A (en) * | 2018-10-12 | 2019-03-29 | 北京交通大学 | A kind of Vacuum Arc propeller based on multianode structure |
| CN109737023A (en) * | 2018-12-10 | 2019-05-10 | 兰州空间技术物理研究所 | A kind of self breakdown type pulsed plasma thruster of annular vertebral body structure anode |
| CN109751212A (en) * | 2019-01-28 | 2019-05-14 | 北京交通大学 | Pulse plasma propeller with microporous insulation anode |
| CN110012584A (en) * | 2019-03-22 | 2019-07-12 | 北京交通大学 | Pulse Vacuum arc plasma propeller with segmentation microporous insulation anode |
| CN111472954A (en) * | 2020-03-25 | 2020-07-31 | 北京交通大学 | Insulating anode cathode arc propeller with auxiliary suspension potential electrode |
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| CN109538431A (en) * | 2018-10-12 | 2019-03-29 | 北京交通大学 | A kind of Vacuum Arc propeller based on multianode structure |
| CN109441747A (en) * | 2018-11-02 | 2019-03-08 | 北京航空航天大学 | A kind of electric propulsion engine sparking mode |
| CN109737023A (en) * | 2018-12-10 | 2019-05-10 | 兰州空间技术物理研究所 | A kind of self breakdown type pulsed plasma thruster of annular vertebral body structure anode |
| CN109751212A (en) * | 2019-01-28 | 2019-05-14 | 北京交通大学 | Pulse plasma propeller with microporous insulation anode |
| CN110012584A (en) * | 2019-03-22 | 2019-07-12 | 北京交通大学 | Pulse Vacuum arc plasma propeller with segmentation microporous insulation anode |
| CN112423460A (en) * | 2019-08-20 | 2021-02-26 | 新奥科技发展有限公司 | Plasma generator |
| CN112423460B (en) * | 2019-08-20 | 2023-03-21 | 新奥科技发展有限公司 | Plasma generator |
| CN111472954A (en) * | 2020-03-25 | 2020-07-31 | 北京交通大学 | Insulating anode cathode arc propeller with auxiliary suspension potential electrode |
| CN111654967A (en) * | 2020-06-09 | 2020-09-11 | 北京交通大学 | Double-jet pulse metal ion plasma propeller |
| 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 |
| CN113357109A (en) * | 2021-06-30 | 2021-09-07 | 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 |
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