CN106351811A - Low-power cylinder-type electromagnetic plasma thruster with adjustable magnetic field - Google Patents
Low-power cylinder-type electromagnetic plasma thruster with adjustable magnetic field Download PDFInfo
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- CN106351811A CN106351811A CN201610812539.6A CN201610812539A CN106351811A CN 106351811 A CN106351811 A CN 106351811A CN 201610812539 A CN201610812539 A CN 201610812539A CN 106351811 A CN106351811 A CN 106351811A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H1/00—Using plasma to produce a reactive propulsive thrust
- F03H1/0037—Electrostatic ion thrusters
- F03H1/0062—Electrostatic ion thrusters grid-less with an applied magnetic field
- F03H1/0075—Electrostatic ion thrusters grid-less with an applied magnetic field with an annular channel; Hall-effect thrusters with closed electron drift
-
- 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
- F03H1/0081—Electromagnetic plasma thrusters
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- Combustion & Propulsion (AREA)
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- General Engineering & Computer Science (AREA)
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Abstract
The invention provides a low-power cylinder-type electromagnetic plasma thruster with an adjustable magnetic field and belongs to the field of electric propulsion. The thruster comprises a front coil, a rear coil, a ceramic discharging channel, a pure iron sleeve, an iron core, a front seal cover, a rear seal cover and others. A discharging chamber formed by the ceramic discharging channel is cylindrical. The front coil and the rear coil are installed in front and back of the ceramic discharging channel respectively, and the distribution of the magnetic field inside the discharging chamber is changed by adjusting the current of the coils. A magnetic guide ring is installed at the outlet end of the ceramic discharging channel, a plasma generating region and an accelerating region inside the discharging chamber are easily separated, ions are fully accelerated, and the specific impulse of the thruster is improved. According to the thruster, a discharging chamber of a common Hall thruster is improved into a complete cylinder, in this way, the annular Hall thruster is high in corrosion rate under low power, ionization efficiency is obviously improved, and the low-power cylinder-type electromagnetic plasma thruster can stably work under 100 W or less and has expanded application in the low-power field compared with the common electric thruster.
Description
Technical field
The invention belongs to electric propulsion field, it is related to a kind of low-power, magnetic field adjustable column type electromagnetism plasma propulsion
Device.
Background technology
Electric propulsion technology has ion propeller and Hall to push away through the development of more than 60 years, more ripe applied product
Enter device etc..Wherein, Hall thruster is slightly inferior to ion propeller in specific impulse and efficiency, but due to its construction and control system more
For simple, become one of the development priority in various countries electric propulsion field.
Conventional Hall thruster adopts ring discharge passage, and when rated power is higher than 100w, completely may be used in circular passage
To meet the demand of space mission.However, with the progressively rise of satellite trend toward miniaturization, designer proposes to propulsion system
Reduce the requirement of power consumption, and conventional electric propulsion device does not almost have the product in below 100w for the power consumption, not to mention a below 50w.
Although people attempt with various methods, conventional Hall thruster being zoomed in and out, keep constant, feature long in loop configuration
Under conditions of degree is scaled, the engine often inefficiency developed, specific impulse is relatively low, or at all can not be work(
Consumption is reduced to below 100w.The main cause causing this problem is, during annular Hall thruster miniaturization, to constrain
Magnetic field intensity needed for electronics and scaling ratio are inversely proportional to, and high-intensity magnetic field needs high-power, large volume permanent magnet or electromagnetism
Producing, this has substantially run counter to the original intention of propeller miniaturization to coil.Moreover, narrow ring discharge passage seriously reduces
Ionizing efficiency, electronics often before reaching anode or colliding with propellant atom just with channel wall collision, make
Wall corrodes, and the corrosion of wall is also the key factor of impact thruster life-span.
Content of the invention
For solving the above problems, the present invention proposes a kind of low-power, magnetic field adjustable column type electromagnetism plasma propulsion
Device.On the basis of conventional Hall thruster, its arc chamber passage is made and sexually revises at all, column type is changed into from annular, from
And change its internal electron the way of restraint, and a solenoid is respectively disposed to adjust magnetic field, to adapt to before and after discharge channel
Different discharge conditions.
A kind of low-power of the present invention, magnetic field adjustable column type electromagnetism plasma propeller, including front capping, front
Snare cylinder, front coil, circular anode, ceramic discharge passage, pure iron sleeve, iron core, rear coil, rear loop sleeve, rear seal-cover, company
Acting flange, air inlet pipe, pad and screw.
Pure iron sleeve inner has raised baffle ring, and ceramic discharge passage is fixed in pure iron sleeve, pure iron sleeve inner convex
Play baffle ring and axially position is carried out to ceramic discharge passage.The arc chamber that described ceramic discharge passage is formed is column type.In pottery
The indoor design of porcelain discharge channel has annular recess, and circular anode embeds described annular groove, with screw by circular anode and
Ceramic discharge passage is fixed, and using one of screw in compression electric wire, can apply positive voltage to circular anode.Described annular is recessed
Have hole on groove, and 3 counterbores equally distributed with circular anode surface are corresponding, 3 air inlet pipe are from the left side of circular anode
Respectively in 3 counterbores of insertion circular anode, and welded seal.
Front coil is put in front loop sleeve, and front loop sleeve is stuck in outside ceramic discharge passage and pure iron sleeve between,
Using bolt, front capping is fixed on pure iron sleeve, loop sleeve before compression；Coil is contained in rear loop sleeve afterwards, loads pure
In ferrum sleeve, leave the gap of 2mm between rear loop sleeve and ceramic discharge passage in order to arrangement before coil electricity
Line.
Counterbore is left on rear seal-cover surface, iron core bolt and pad is fixed on rear seal-cover by counterbore, more directly blocks
In rear loop sleeve, after installation, there is the distance of 1mm between iron core and ceramic discharge passage；The positive and negative two-stage of front coil
All from rear seal-cover, corresponding aperture enters.Described rear seal-cover, rear loop sleeve and pure iron sleeve pass through adpting flange, profit
Fixed with screw-driving.
On here basis, the present invention also has made some improvements to ceramic discharge chamber, adds in ceramic discharge chamber outlet end
One magnetic conductance ring, but keep arc chamber length and internal diameter constant.Described magnetic conductance ring is made by high temperature resistant soft magnetic materials.
3 described air inlet pipe are formed by 1 air inlet pipe shunting outside described propeller, and such setting both can be very
Easily control anode propellant flow rate it is also possible to make the indoor propellant of electric discharge be evenly distributed.
Advantages of the present invention and having the active effect that
1st, it is directed to annular Hall thruster to be difficult to for power to be reduced to 100w problem below, present invention eliminates annular is suddenly
The angle of rake newel of that, arc chamber is become column type, and solves annular Hall thruster and corrode under low-power
The higher problem of rate.Propeller ionizing efficiency after improvement is obviously improved, and can be in below 100w steady operation, can conduct
The spacecraft posture adjustment such as microsatellite, the power resources of change rail, have expanded the application in low-power field for the conventional electromagnetic propeller.
2nd, column type electromagnetism plasma propeller low-profile, lighter weight, internal structure is compact, former and later two electromagnetism
The arrangement of coil can easily adjust magnetic field shape and size.
3rd, the structure of rear loop sleeve both provides suitable position for coil after being wound around, and is also air inlet pipe and electric wire offer
Sufficient space, has intercepted the contact that coil is with air inlet pipe, has prevented short circuit.
4th, front loop sleeve one side can as be wound around before coil skeleton, on the other hand due to it be pure iron processing and
Become, expand the adsorption area of front end magnetic circuit so that the magnetic field of arc chamber near wall is approximately perpendicular to wall, greatly lifted
The radial component in the indoor magnetic field of electric discharge, is conducive to the constraint of electronics, increases propellant ionization rate.
5th, on the premise of not changing arc chamber length and internal diameter, embed by high temperature resistant soft magnetism in ceramic discharge chamber outlet end
After the magnetic conductance ring that material is made, the indoor magnetic field structure of electric discharge can be optimized, local lifting arc chamber exports near wall region
Magnetic field intensity, is conducive to the separation of ion ionized region and accelerating region, lifts propeller specific impulse.
Brief description
Fig. 1 is the sectional arrangement drawing of column type electromagnetism plasma propeller of the present invention；
Fig. 2 is the propeller sectional view that the present invention with the addition of magnetic conductance ring.
In figure:
Coil 4- circular anode 5- ceramic discharge passage before loop sleeve 3- before capping 2- before 1-
Loop sleeve 10- rear seal-cover after coil 9- after 6- pure iron sleeve 7- iron core 8-
11- adpting flange 12- air inlet pipe 13- pad 14- screw 15- magnetic conductance ring
Specific embodiment
With reference to specific embodiments and the drawings, technical scheme is illustrated.
Specific embodiment one: with reference to Fig. 1, present embodiment is illustrated, a kind of low-power of present embodiment, magnetic
The adjustable column type electromagnetism plasma propeller in field, including front capping 1, front loop sleeve 2, front coil 3, circular anode 4, pottery
Porcelain discharge channel 5, pure iron sleeve 6, iron core 7, rear coil 8, rear loop sleeve 9, rear seal-cover 10, adpting flange 11, air inlet pipe 12,
Pad 13 and screw 14；Wherein, the arc chamber that ceramic discharge passage 5 is formed is column type.
There is raised baffle ring, on the basis of pure iron sleeve 6, ceramic discharge passage 5 is fixed on pure iron sleeve inside pure iron sleeve 6
In 6, the raised baffle ring within pure iron sleeve 6 carries out axially position to ceramic discharge passage 5.Front loop sleeve 2 put into by front coil 3
Interior, front loop sleeve 2 is stuck between ceramic discharge passage 5 outside and pure iron sleeve 6, is fixed on front capping 1 using bolt pure
On ferrum sleeve 6, both play the effect of loop sleeve 2 before compression, also save the space needed for the connectors such as bolt.Put in pottery
The inside of electric channel 5, circular anode 4 is embedded pre-designed annular recess, with 3 Screws on the left of circular anode 4
Circular anode 4 and ceramic discharge passage 5 are tightened fixation, using one of screw in compression electric wire it is possible to circular anode 4
Apply positive voltage, and because ceramic discharge passage 5 has insulating properties in itself, this circuit connects will not be sent out with front and back's coil
Raw short circuit；3 air inlet pipe 12 are from the circular anode 4 equally distributed counterbore in left side insertion circular anode 4 surface, and welded seal.3
Root air inlet pipe is formed by 1 trachea shunting outside described propeller, and such setting both can easily control anode to push away
Enter agent flux it is also possible to make the indoor propellant of electric discharge be evenly distributed；Note ensureing that 3 air inlet pipe 12 pass through on rear seal-cover 10
Corresponding aperture.
The rear coil 8 winding is contained in rear loop sleeve 9, loads in pure iron sleeve 6 in the lump, after installing, rear line
Also leave the gap of 2mm between snare cylinder 9 and ceramic discharge passage 5 in order to arrangement before coil 3 electric wire, front coil 3
Positive and negative two-stage all from rear seal-cover 10 corresponding aperture enter.Counterbore is also left on rear seal-cover 10 surface, convenient installation iron core 7,
After both are fixed with bolt and pad, can be directly clamped among in rear loop sleeve 9, after installation, iron core 7 and pottery are put
There is the distance of 1mm between electric channel 5.Finally, will be right with rear seal-cover 10, rear loop sleeve 9 and pure iron sleeve 6 for adpting flange 11
Standard, is fixed using screw-driving.Because rear coil 8 number of turn is more, it is wound around closely, the heat that therefore described propeller produces is concentrated
In afterbody, adpting flange 11 is conducive to heat to transmit to external support using brass material.
Front coil 3 and rear coil 8 are entwined according to certain number of turn by copper wire, and when changing coil current, electric discharge is logical
Magnetic field in road 5 changes therewith, can adjust magnetic field so as to reach optimum state according to angle of rake operating mode of the present invention.
Front loop sleeve 2 is formed by pure iron materials processing, and magnetic conductivity is excellent, is placed in discharge channel 5 periphery, on the one hand can increase magnetic
Line of force adsorption area, makes the magnetic field radial component in discharge channel 5 increase, and is conducive to preferably about beam electrons；On the other hand, front
Loop sleeve 2, as the skeleton of front coil 3, facilitates winding and the fixation of copper wire.The effect of loop sleeve 9 and front loop sleeve afterwards
2 are similar to, but material therefor is common stainless steel, and magnetic conductivity is poor, is not enough to become a part for magnetic circuit；With pure iron sleeve 6 even
Connect the fixing 2mm gap later left, installation and the electric wire arrangement of admission line can be met completely.
Front capping 1, pure iron sleeve 6, rear seal-cover 10 and iron core 7 are formed by pure iron materials processing, constitute described propulsion
The Primary magnetic circuit of device, the most of magnetic line of force being produced by described front coil 3 and rear coil 8 will pass through from aforementioned 4 parts,
To ensure the indoor certain magnetic field intensity of electric discharge.Wherein, iron core 7 adopts front fine and rear thick structure, can converge to the full extent
Poly- magnetic field, save space.The arrangement of whole magnetic circuit can be in the larger magnetic field of the indoor formation radial component of electric discharge, near axis
Neighbouring region forms magnetic mirror, electronics is carried out operative constraint with this, improves propellant ionization rate.3 air inlet pipe 12 are respectively
Insertion is distributed on 3 air inlets of circular anode 4 left-hand face, makes propellant indoor even into electric discharge, when imposing to anode
During positive voltage, the electronics by electric field gravitational attraction will be strongly to anode movement, and propellant atom collides, and produces ion,
, in the presence of electric field force, Accelerating Removal propeller, thus form thrust for ion.The adpting flange 11 of described propeller afterbody by
Pyrite is made, and heat conductivity is good, is propeller and the external support necessary connection of offer.
Specific embodiment two: with reference to Fig. 2, present embodiment is illustrated, on the basis of embodiment one, pottery
Step is left in discharge channel 5 exit, and magnetic conductance ring 15 utilizes friction tight mode to embed step, and keeps arc chamber length and interior
Footpath is constant.Compare with embodiment one, under identical coil current, the indoor magnetic field structure of electric discharge is optimized, and locally carries
Rise the magnetic field intensity that arc chamber exports near wall region, reduce the corrosion to arc chamber wall for the electronics, and due to local magnetic field gradient
It is changed on the occasion of accelerating region is able to separate with ionized region so that ion can obtain abundant acceleration, improves propeller ratio from negative value
Punching.
In accordance with following steps, the present invention gets final product normal work:
1st, external cathode and described column type electromagnetism plasma propeller are together fixed on outside support, adjust two
The relative position of person, makes external cathode apart from propeller axis 5～8cm, negative electrode axis and 30～50 degree of propeller axis angle；
2nd, prefiring is carried out to external cathode so as to can stable launching electronics, and emission current maintains the level of 1a；
3rd, front coil 3 and rear coil 8 are powered, lead to the electric current of upper 1a and 2a respectively, and the sense of current is consistent；
4th, after before and after's coil working is stable, it is described propeller supply propellant, generally xenon, in the shock of electronics
Under, atom occurs ionization to generate plasma, and its intermediate ion, via electric field acceleration, sprays ceramic discharge passage 5, forms thrust.
Claims (10)
1. a kind of low-power, magnetic field adjustable column type electromagnetism plasma propeller it is characterised in that: include before capping, front
Loop sleeve, front coil, circular anode, ceramic discharge passage, pure iron sleeve, iron core, rear coil, rear loop sleeve, rear seal-cover,
Adpting flange, air inlet pipe, pad and screw；The arc chamber that described ceramic discharge passage is formed is column type；
Pure iron sleeve inner has raised baffle ring, and ceramic discharge passage is fixed in pure iron sleeve, the raised gear of pure iron sleeve inner
Ring carries out axially position to ceramic discharge passage；There is annular recess in the indoor design of ceramic discharge passage, circular anode embeds
Circular anode and ceramic discharge passage are fixed by described annular groove with screw, using one of screw in compression electric wire, right
Circular anode applies positive voltage；Have hole on described annular groove, and 3 counterbores equally distributed with circular anode surface are relative
Should, 3 air inlet pipe are from 3 counterbores that circular anode is inserted in the left side of circular anode respectively, and welded seal；
Front coil is put in front loop sleeve, and front loop sleeve is stuck in outside ceramic discharge passage and pure iron sleeve between, utilizes
Front capping is fixed on pure iron sleeve bolt, loop sleeve before compression；Coil is contained in rear loop sleeve afterwards, loads pure iron set
In cylinder, between rear loop sleeve and ceramic discharge passage, leave the gap of 2mm；Counterbore is left on rear seal-cover surface, by iron core spiral shell
Bolt and pad are fixed on rear seal-cover by counterbore, then are directly clamped among in rear loop sleeve, between iron core and ceramic discharge passage
There is the distance of 1mm；The positive and negative two-stage of front coil corresponding aperture all from rear seal-cover enters；
Described rear seal-cover, rear loop sleeve and pure iron sleeve pass through adpting flange, are fixed using screw-driving.
2. a kind of low-power according to claim 1, magnetic field adjustable column type electromagnetism plasma propeller, its feature
It is: the structure of described column type electromagnetism plasma propeller also includes magnetic conductance ring, in described ceramic discharge channel outlet
Place leaves step, and magnetic conductance ring embeds in step, keeps arc chamber length and internal diameter constant；Described magnetic conductance ring is by high temperature resistant soft magnetism material
Material is made.
3. a kind of low-power according to claim 1 and 2, magnetic field adjustable column type electromagnetism plasma propeller, its
Be characterised by: the rated power of described column type electromagnetism plasma propeller in below 100w, by adjust front coil and after
The electric current of coil changes the indoor Distribution of Magnetic Field of electric discharge.
4. a kind of low-power according to claim 1, magnetic field adjustable column type electromagnetism plasma propeller, its feature
It is: described front loop sleeve is made using pure iron material.
5. a kind of low-power according to claim 1, magnetic field adjustable column type electromagnetism plasma propeller, its feature
It is: described rear loop sleeve is made using common stainless steel.
6. a kind of low-power according to claim 1, magnetic field adjustable column type electromagnetism plasma propeller, its feature
It is: described front capping, pure iron sleeve, rear seal-cover and iron core are formed by pure iron materials processing.
7. a kind of low-power according to claim 1, magnetic field adjustable column type electromagnetism plasma propeller, its feature
It is: described iron core adopts front fine and rear thick structure.
8. a kind of low-power according to claim 1, magnetic field adjustable column type electromagnetism plasma propeller, its feature
It is: 3 described air inlet pipe are formed by 1 air inlet pipe shunting outside described column type electromagnetism plasma propeller.
9. a kind of low-power according to claim 1, magnetic field adjustable column type electromagnetism plasma propeller, its feature
It is: described adpting flange is made using brass material.
10. the low-power described in a kind of application claim 1 or 2, magnetic field adjustable column type electromagnetism plasma propeller
Method of work it is characterised in that: comprise the following steps:
Step 1: external cathode and described column type electromagnetism plasma propeller are together fixed on outside support, adjust two
The relative position of person, makes external cathode apart from propeller axis 5～8cm, negative electrode axis and 30～50 degree of propeller axis angle；
Step 2: prefiring is carried out to external cathode so as to stable launching electronics, and emission current maintains the level of 1a；
Step 3: front coil and rear coil are powered, lead to the electric current of upper 1a and 2a respectively, and the sense of current is consistent；
Step 4: after front coil and after coil working stable after, be described propeller supply propellant, under the shock of electronics, former
Son occurs ionization to generate plasma, and its intermediate ion, via electric field acceleration, sprays ceramic discharge passage, forms thrust.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610812539.6A CN106351811B (en) | 2016-09-09 | 2016-09-09 | A kind of low-power, the adjustable cylindrical type electromagnetism plasma propeller in magnetic field |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610812539.6A CN106351811B (en) | 2016-09-09 | 2016-09-09 | A kind of low-power, the adjustable cylindrical type electromagnetism plasma propeller in magnetic field |
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| CN106351811A true CN106351811A (en) | 2017-01-25 |
| CN106351811B CN106351811B (en) | 2019-01-11 |
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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106968906A (en) * | 2017-04-27 | 2017-07-21 | 河南理工大学 | Plasma propulsion device |
| CN107044396A (en) * | 2017-06-14 | 2017-08-15 | 北京航空航天大学 | A kind of water-cooling structure complementary field magnetic plasma propeller |
| CN107165794A (en) * | 2017-06-12 | 2017-09-15 | 北京航空航天大学 | A kind of adjustable low-power hall thruster with magnetic screening effect in magnetic field |
| CN107178790A (en) * | 2017-05-26 | 2017-09-19 | 哈尔滨工程大学 | Electric lens guiding plasma generator |
| CN107605687A (en) * | 2017-09-28 | 2018-01-19 | 哈尔滨工业大学深圳研究生院 | Low-power electric arc heated propeller |
| CN107725296A (en) * | 2017-09-01 | 2018-02-23 | 兰州空间技术物理研究所 | A kind of adjustable permanent magnetism hall thruster magnetic structure of magnetic induction intensity |
| 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 |
| CN109826768A (en) * | 2019-02-27 | 2019-05-31 | 哈尔滨工业大学 | A kind of low-power cylinder hall thruster of diamond wall surface |
| CN111120232A (en) * | 2018-11-01 | 2020-05-08 | 哈尔滨工业大学 | Cusped field plasma thruster capable of realizing fine adjustment and discharge control performance |
| CN111140400A (en) * | 2019-12-23 | 2020-05-12 | 北京航空航天大学 | Anode air inlet assembly of electric propulsion engine |
| CN111219305A (en) * | 2019-03-21 | 2020-06-02 | 哈尔滨工业大学 | Hall thruster with novel buffer cavity |
| CN112431732A (en) * | 2020-11-20 | 2021-03-02 | 北京航空航天大学 | Double-magnetic-ring micro cylindrical Hall thruster for friction welding anode |
| CN113931818A (en) * | 2021-11-04 | 2022-01-14 | 中国人民解放军战略支援部队航天工程大学 | Device and method for improving ion density in space electric thruster |
| CN114135455A (en) * | 2021-11-22 | 2022-03-04 | 北京星辰空间科技有限公司 | Single-coil magnetic shielding low-power Hall thruster |
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Cited By (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106968906A (en) * | 2017-04-27 | 2017-07-21 | 河南理工大学 | Plasma propulsion device |
| CN107178790A (en) * | 2017-05-26 | 2017-09-19 | 哈尔滨工程大学 | Electric lens guiding plasma generator |
| CN107165794A (en) * | 2017-06-12 | 2017-09-15 | 北京航空航天大学 | A kind of adjustable low-power hall thruster with magnetic screening effect in magnetic field |
| CN107165794B (en) * | 2017-06-12 | 2019-10-01 | 北京航空航天大学 | A kind of adjustable low-power hall thruster with magnetic screening effect in magnetic field |
| CN107044396A (en) * | 2017-06-14 | 2017-08-15 | 北京航空航天大学 | A kind of water-cooling structure complementary field magnetic plasma propeller |
| CN107725296A (en) * | 2017-09-01 | 2018-02-23 | 兰州空间技术物理研究所 | A kind of adjustable permanent magnetism hall thruster magnetic structure of magnetic induction intensity |
| CN107605687A (en) * | 2017-09-28 | 2018-01-19 | 哈尔滨工业大学深圳研究生院 | Low-power electric arc heated propeller |
| 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 |
| CN111120232A (en) * | 2018-11-01 | 2020-05-08 | 哈尔滨工业大学 | Cusped field plasma thruster capable of realizing fine adjustment and discharge control performance |
| CN109826768B (en) * | 2019-02-27 | 2020-04-24 | 哈尔滨工业大学 | Cylindrical hall thrustor of low power of diamond wall |
| CN109826768A (en) * | 2019-02-27 | 2019-05-31 | 哈尔滨工业大学 | A kind of low-power cylinder hall thruster of diamond wall surface |
| CN111219305A (en) * | 2019-03-21 | 2020-06-02 | 哈尔滨工业大学 | Hall thruster with novel buffer cavity |
| CN111219305B (en) * | 2019-03-21 | 2021-06-15 | 哈尔滨工业大学 | Hall thruster with buffer cavity |
| CN111140400A (en) * | 2019-12-23 | 2020-05-12 | 北京航空航天大学 | Anode air inlet assembly of electric propulsion engine |
| CN111140400B (en) * | 2019-12-23 | 2021-10-22 | 北京航空航天大学 | Anode air inlet assembly of electric propulsion engine |
| CN112431732A (en) * | 2020-11-20 | 2021-03-02 | 北京航空航天大学 | Double-magnetic-ring micro cylindrical Hall thruster for friction welding anode |
| CN112431732B (en) * | 2020-11-20 | 2021-08-20 | 北京航空航天大学 | Double-magnetic-ring micro cylindrical Hall thruster for friction welding anode |
| CN113931818A (en) * | 2021-11-04 | 2022-01-14 | 中国人民解放军战略支援部队航天工程大学 | Device and method for improving ion density in space electric thruster |
| CN113931818B (en) * | 2021-11-04 | 2024-01-02 | 中国人民解放军战略支援部队航天工程大学 | Device and method for improving ion density in space electric thruster |
| CN114135455A (en) * | 2021-11-22 | 2022-03-04 | 北京星辰空间科技有限公司 | Single-coil magnetic shielding low-power Hall thruster |
| CN114135455B (en) * | 2021-11-22 | 2024-04-19 | 北京星辰空间科技有限公司 | Single-coil magnetic shielding low-power Hall thruster |
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| CN106351811B (en) | 2019-01-11 |
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