CN106968906A - A kind of plasma propulsion device - Google Patents
A kind of plasma propulsion device Download PDFInfo
- Publication number
- CN106968906A CN106968906A CN201710285710.7A CN201710285710A CN106968906A CN 106968906 A CN106968906 A CN 106968906A CN 201710285710 A CN201710285710 A CN 201710285710A CN 106968906 A CN106968906 A CN 106968906A
- Authority
- CN
- China
- Prior art keywords
- arc chamber
- microwave
- propulsion device
- plasma propulsion
- plasma
- 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.)
- Pending
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
- F03H1/0081—Electromagnetic plasma thrusters
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Electromagnetism (AREA)
- Plasma & Fusion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Plasma Technology (AREA)
Abstract
The invention belongs to plasma propulsion technical field, more particularly to a kind of plasma propulsion device, the magnetic line of force circumnutation that magnetic circuit system in the arc chamber on its inwall is produced electronically forms ECR resonance regions, the arc chamber imports microwave through microwave input system, the present invention solve prior art exist especially for microsatellite for, because the electrical power of offer is small, electric field energy is not enough, so as to cause gas breakdown spread of voltage and cause the density and efficiency of the plasma of gas discharge generation lower, therefore, cause the less problem of thrust ratio of satellite, with avoiding cathode burning corrosion, extend the service life of satellite, simultaneously because discharging efficiency is high, so that the utilization ratio of propellant is high, thrust is stable, the advantageous effects of reliability height etc..
Description
Technical field
The invention belongs to plasma propulsion technical field, more particularly to a kind of plasma propulsion device.
Background technology
Electric propulsion system chemical system is compared, with than leaping high, thrust is low and power consumption more than the features such as, the specific impulse of electric propulsion is led to
Often higher than chemical propulsion system, the propellant that it completes same required by task is just few, so as to increase having for spacecraft
Load, or increase propellant carrying amount are imitated to extend the service life of spacecraft, the thrust of electric propulsion system is low, to spacecraft
Disturbance it is small, control accuracy is high, but the working time is longer than the chemical propulsion system of high thrust, therefore it is required that electric propulsion system
It is long-life, highly reliable.
Electric thruster is the kernel subsystems of electric propulsion system, and by the difference of propellant accelerated mode, it can be divided into electricity
Hot type, electrostatic and electromagnetic type three major types, electrostatic ion thruster are to accelerate charged particle using electrostatic field, are sprayed at a high speed
Ion beam current produce reaction force be thruster thrust, magnetic field is usually used to about beam electrons, the spy of electrostatic thruster
Point be than leaping high, compact conformation, light weight and technology maturation etc., and electron cyclotron resonace thruster is to belong to ion thrust
Device, existing electric propulsion device has cathode burning corrosion, and electronic and ionic density is low, and the life-span has the shortcomings that limitation.
For prior art is present especially for microsatellite, because the electrical power of offer is small, electric field energy is not enough, from
And cause gas breakdown spread of voltage and cause the density and efficiency of the plasma of gas discharge generation lower, therefore, lead
Cause the less problem of thrust ratio of satellite.
The content of the invention
The present invention provides a kind of plasma propulsion device, exists to solve to propose prior art in above-mentioned background technology
For microsatellite, because the electrical power of offer is small, electric field energy is not enough, so as to cause gas breakdown voltage not
The density and efficiency of plasma that is stable and causing gas discharge generation are lower, therefore, cause the thrust ratio of satellite less
Problem.
Technical problem solved by the invention is realized using following technical scheme：A kind of plasma propulsion device, bag
The magnetic line of force circumnutation for including the generation of the magnetic circuit system in arc chamber, the arc chamber on its inwall is electronically formed
ECR resonance regions, the arc chamber imports microwave through microwave input system.
Further, the microwave frequency and electron gyro-frequency are equal.
Further, connection working medium in the arc chamber.
Further, the microwave that microwave input system is imported enters arc chamber through feedback window.
Further, the arc chamber input is connected to microwave input system, and the arc chamber circumferential inner wall is connected to production
The magnetic circuit system of magnetisation, the arc chamber is connected to grid system.
Further, the arc chamber flare.
Further, the grid system includes positive potential screen, the accelerating grid for extracting ion beam current with kilovolt
With the decelerating screen of zero potential, the screen is connected to arc chamber positive pole, and the accelerating grid is connected to arc chamber negative pole, the deceleration
Grid are grounded.
Further, the microwave input system includes coaxial cable, and the coaxial cable input is connected to microwave source, its
Output end and the coupling probe of cylindrical waveguide formation are connected to arc chamber.
Further, the magnetic circuit system is made up of magnet, yoke and gap.
Further, the magnet uses samarium cobalt permanent magnet body.
Advantageous effects：
1st, the magnetic line of force that this patent is produced using the magnetic circuit system in the arc chamber on its inwall does the electricity of circumnutation
Son forms ECR resonance regions, and the arc chamber imports microwave, microwave frequency and the electron gyro-frequency phase through microwave input system
Deng connection working medium in, the arc chamber, the microwave that microwave input system is imported enters arc chamber through feedback window, because electronics exists
Circumnutation is done around the magnetic line of force in ECR resonance regions.Microwave enters from pole form guide, enters tubaeform arc chamber by feedback window.
When the microwave frequency and equal electron gyro-frequency of input, microwave resonates with electronics, at a high speed rotation electronics constantly with
Working medium particle occurs inelastic collision so that working medium is ionized, so that plasma is formed, because present invention research is a kind of new
The electron cyclotron resonace ion thruster of type, because electron cyclotron resonace thruster has without cathodic discharge scheme, it is to avoid the moon
Pole ablation, extends the service life of satellite, simultaneously because discharging efficiency is high, so that the utilization ratio of propellant is high, and thrust
It is stable, high reliability, and then overcome in the prior art and have that electrical power is small, electric field energy is not enough, so as to cause gas
Bulk breakdown voltage is unstable and causes the density and efficiency of the plasma of gas discharge generation lower, therefore, causes satellite
The less problem of thrust ratio.
2nd, this patent is connected to microwave input system, the arc chamber circumferential inner wall connection using arc chamber input
Magnetic circuit system for producing magnetic field, the arc chamber is connected to grid system, because arc chamber is by microwave input system, loudspeaker
Shape arc chamber, magnet and grid system composition, because magnet is embedded in tubaeform electric discharge chamber interior walls, to produce one stronger
Field region mouthful, the effect of tubaeform arc chamber：（1）Ionized gas, generates the sufficiently high plasma of density, to meet extraction
The need for beam current density；（2）Grid is extracted from plasma boundary, accelerated, focusing forms high speed plasma beam.
3rd, this patent includes the positive potential screen with kilovolt, for extracting adding for ion beam current using the grid system
The decelerating screen of fast grid and zero potential, the screen is connected to arc chamber positive pole, and the accelerating grid is connected to arc chamber negative pole, described
Decelerating screen is grounded, and is screen, accelerating grid and decelerating screen respectively, wherein screen is with putting because grid system is made up of three grids
Electric room is joined directly together, and band is higher than loading negative potential on the positive potential of kilovolt, accelerating grid and is used to produce sufficiently strong electric field to extract
Ion beam current, the direction of the ion of extraction along power line accelerates to produce thrust, and decelerating screen is usually zero potential, with acceleration
Grid formation electric field realizes the deceleration of ion beam current.
4th, this patent microwave input system is main is made up of coaxial cable, coupling probe, cylindrical waveguide and electric discharge room housing.
Microwave source connection coaxial cable constitutes the microwave transmission system outside arc chamber, and the inner wire of coaxial cable gos deep into cylindrical waveguide
Coupling probe is formed, microwave input system uses cylindrical waveguide, and cylindrical waveguide is the best transmission mode of microwave, corresponding main mould
TE10 moulds are rational transmission means, when the frequency of microwave is 2.45GHz, microwave attenuation very little, microwave coupling to arc chamber
Efficiency comparison is high, and arc chamber can obtain highest microwave power.
5th, this patent magnetic circuit is made up of magnet, yoke and gap.When designing magnetic circuit magnetic field, produced using samarium cobalt permanent magnet body
Magnetic field in raw arc chamber.Because samarium cobalt permanent magnet body is a kind of alloy material, big with coercivity, demagnetization temperature is high, performance
Stable advantage, is relatively specific for the condition of work of arc chamber.
6th, the microwave that this patent is imported using microwave input system enters arc chamber through feedback window, because feedback window is using circle
Pole form guide, is optimal transmission means, maximal efficiency by microwave coupling to arc chamber, arc chamber is obtained maximum microwave
Power.
Brief description of the drawings
Fig. 1 is a kind of structural representation of plasma propulsion device of the invention；
Fig. 2 is a kind of grid system electrical schematic diagram of plasma propulsion device of the invention；
Fig. 3 is a kind of structural representation of the magnetic circuit system of plasma propulsion device of the invention.
Embodiment
The present invention is described further below in conjunction with accompanying drawing：
In figure：1- arc chambers, 2- magnetic circuit systems, 3-ECR resonance regions, 4- microwave input systems, 5- working medium, 6- grid systems, 7-
Screen, 8- accelerating grids, 9- decelerating screens, 10- coaxial cables, 11- microwave sources, 12- cylindrical waveguides, 13- coupling probes, 14- magnets,
15- yokes, 16- gaps.
Embodiment：
The present embodiment：As shown in figure 1, a kind of plasma propulsion device, including arc chamber 1, the arc chamber 1 is interior to be surrounded in it
The magnetic line of force circumnutation that magnetic circuit system 2 on wall is produced electronically forms ECR resonance regions 3, and the arc chamber 1 is defeated through microwave
Enter system 4 and import microwave.
The microwave frequency and electron gyro-frequency are equal.
Connection working medium 5 in the arc chamber 1.
The microwave that microwave input system 4 is imported enters arc chamber 1 through feedback window.
Because the magnetic line of force produced using the magnetic circuit system in the arc chamber on its inwall does the electricity of circumnutation
Son forms ECR resonance regions, and the arc chamber imports microwave, microwave frequency and the electron gyro-frequency phase through microwave input system
Deng connection working medium in, the arc chamber, the microwave that microwave input system is imported enters arc chamber through feedback window, because electronics exists
Circumnutation is done around the magnetic line of force in ECR resonance regions.Microwave enters from pole form guide, enters tubaeform arc chamber by feedback window.
When the microwave frequency and equal electron gyro-frequency of input, microwave resonates with electronics, at a high speed rotation electronics constantly with
Working medium particle occurs inelastic collision so that working medium is ionized, so that plasma is formed, because present invention research is a kind of new
The electron cyclotron resonace ion thruster of type, because electron cyclotron resonace thruster has without cathodic discharge scheme, it is to avoid the moon
Pole ablation, extends the service life of satellite, simultaneously because discharging efficiency is high, so that the utilization ratio of propellant is high, and thrust
It is stable, high reliability, and then overcome in the prior art and have that electrical power is small, electric field energy is not enough, so as to cause gas
Bulk breakdown voltage is unstable and causes the density and efficiency of the plasma of gas discharge generation lower, therefore, causes satellite
The less problem of thrust ratio.
The input of arc chamber 1 is connected to microwave input system 4, and the circumferential inner wall of arc chamber 1 is connected to produce magnetic
The magnetic circuit system 2 of field, the arc chamber 1 is connected to grid system 6.
Due to being connected to microwave input system using arc chamber input, the arc chamber circumferential inner wall is connected to production
The magnetic circuit system of magnetisation, the arc chamber is connected to grid system, because arc chamber is by microwave input system, tubaeform electric discharge
Room, magnet and grid system composition, magnet are embedded in tubaeform electric discharge chamber interior walls, to produce a stronger field region.
The flare of arc chamber 1.
The grid system 6 includes positive potential screen 7, the accelerating grid 8 and zero for extracting ion beam current with kilovolt
The decelerating screen 9 of current potential, the screen 7 is connected to the positive pole of arc chamber 1, and the accelerating grid 8 is connected to the negative pole of arc chamber 1, described to subtract
Fast grid 9 are grounded.
Due to including positive potential screen, the accelerating grid for extracting ion beam current with kilovolt using the grid system
With the decelerating screen of zero potential, the screen is connected to arc chamber positive pole, and the accelerating grid is connected to arc chamber negative pole, the deceleration
Grid are grounded, and are screen, accelerating grid and decelerating screen, wherein screen and arc chamber respectively because grid system is made up of three grids
It is joined directly together, band is higher than loading negative potential on the positive potential of kilovolt, accelerating grid and is used to produce sufficiently strong electric field to extract ion
Line, the direction of the ion of extraction along power line accelerates to produce thrust, and decelerating screen is usually zero potential, with accelerating grid shape
The deceleration of ion beam current is realized into electric field.
The microwave input system 4 includes coaxial cable 10, and the input of coaxial cable 10 is connected to microwave source 11, its
Output end and the coupling probe 13 of the formation of cylindrical waveguide 12 are connected to arc chamber 1.
It is made up of because microwave input system is main coaxial cable, coupling probe, cylindrical waveguide and electric discharge room housing.Microwave
Source connection coaxial cable constitutes the microwave transmission system outside arc chamber, and the inner wire of coaxial cable gos deep into formation in cylindrical waveguide
Coupling probe.
The magnetic circuit system 2 is made up of magnet 14, yoke 15 and gap 16.
The magnet 14 is using samarium cobalt permanent magnet body 14.
Because magnetic circuit is made up of magnet, yoke and gap, when designing magnetic circuit magnetic field, put using samarium cobalt permanent magnet body to produce
Electric interior magnetic field, because samarium cobalt permanent magnet body is a kind of alloy material, big with coercivity, demagnetization temperature is high, and performance is stable
Advantage, be relatively specific for the condition of work of arc chamber.
Operation principle：
The magnetic line of force that this patent is produced by the magnetic circuit system in the arc chamber on its inwall does the electronics of circumnutation
ECR resonance regions are formed, the arc chamber imports microwave, microwave frequency and the electron gyro-frequency phase through microwave input system
Deng connection working medium in, the arc chamber, the microwave that microwave input system is imported enters arc chamber through feedback window, because electronics exists
Circumnutation is done around the magnetic line of force in ECR resonance regions.Microwave enters from pole form guide, enters tubaeform arc chamber by feedback window.
When the microwave frequency and equal electron gyro-frequency of input, microwave resonates with electronics, at a high speed rotation electronics constantly with
Working medium particle occurs inelastic collision so that working medium is ionized, so that plasma is formed, because present invention research is a kind of new
The electron cyclotron resonace ion thruster of type, because electron cyclotron resonace thruster has without cathodic discharge scheme, it is to avoid the moon
Pole ablation, extends the service life of satellite, and the present invention is solved for prior art is present especially for microsatellite, by
In the electrical power of offer is small, electric field energy is not enough, so as to cause gas breakdown spread of voltage and cause what gas discharge was produced
The density and efficiency of plasma are lower, therefore, cause the less problem of thrust ratio of satellite, with avoiding cathode burning corrosion,
The service life of satellite is extended, simultaneously because discharging efficiency is high, so that the utilization ratio of propellant is high, thrust is stable, can
By the advantageous effects of property height etc..
Using technical scheme, or those skilled in the art is under the inspiration of technical solution of the present invention, design
Go out similar technical scheme, and reach above-mentioned technique effect, be to fall into protection scope of the present invention.
Claims (10)
1. the magnetic circuit system in a kind of plasma propulsion device, including arc chamber, the arc chamber on its inwall is produced
Magnetic line of force circumnutation electronically form ECR resonance regions, the arc chamber imports microwave through microwave input system.
2. a kind of plasma propulsion device according to claim 1, it is characterised in that the microwave frequency and electronics are returned
Revolve frequency equal.
3. a kind of plasma propulsion device according to claim 1, it is characterised in that connection work in the arc chamber
Matter.
4. a kind of plasma propulsion device according to claim 1, it is characterised in that it is micro- that microwave input system is imported
Ripple enters arc chamber through feedback window.
5. a kind of plasma propulsion device according to claim 1, it is characterised in that the arc chamber input is connected to
Microwave input system, the arc chamber circumferential inner wall is connected to produce the magnetic circuit system in magnetic field, and the arc chamber is connected to grid
Electrode systems.
6. a kind of plasma propulsion device according to claim 1, it is characterised in that the arc chamber flare.
7. a kind of plasma propulsion device according to claim 5, it is characterised in that the grid system includes having
Kilovolt positive potential screen, the decelerating screen of the accelerating grid for extracting ion beam current and zero potential, the screen is connected to electric discharge
Room positive pole, the accelerating grid is connected to arc chamber negative pole, the decelerating screen ground connection.
8. a kind of plasma propulsion device according to claim 5, it is characterised in that the microwave input system includes
Coaxial cable, the coaxial cable input is connected to microwave source, and the coupling probe that its output end is formed with cylindrical waveguide is connected
In arc chamber.
9. a kind of plasma propulsion device according to claim 5, it is characterised in that the magnetic circuit system by magnet,
Yoke and gap composition.
10. a kind of plasma propulsion device according to claim 9, it is characterised in that the magnet uses SmCo forever
Magnet.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710285710.7A CN106968906A (en) | 2017-04-27 | 2017-04-27 | A kind of plasma propulsion device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710285710.7A CN106968906A (en) | 2017-04-27 | 2017-04-27 | A kind of plasma propulsion device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106968906A true CN106968906A (en) | 2017-07-21 |
Family
ID=59332830
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710285710.7A Pending CN106968906A (en) | 2017-04-27 | 2017-04-27 | A kind of plasma propulsion device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106968906A (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107559164A (en) * | 2017-08-25 | 2018-01-09 | 上海航天控制技术研究所 | A kind of change propulsive microwave ECR propulsion system and method |
| CN109681399A (en) * | 2018-12-12 | 2019-04-26 | 上海航天控制技术研究所 | A kind of minor diameter efficient microwave ECR averager |
| CN110145446A (en) * | 2019-06-13 | 2019-08-20 | 哈尔滨工业大学 | A kind of micro- ox propulsion device of pulse electrical excitation |
| CN111306024A (en) * | 2020-02-14 | 2020-06-19 | 哈尔滨工业大学 | Microwave ion propulsion unit based on lateral wall cusped magnetic field |
| CN111456921A (en) * | 2019-01-22 | 2020-07-28 | 哈尔滨工业大学 | Microwave enhancement-based field emission thruster |
| CN111706482A (en) * | 2020-06-28 | 2020-09-25 | 哈尔滨工业大学 | Ion wind thrust device cooperated with microwave |
| CN112555112A (en) * | 2020-11-06 | 2021-03-26 | 兰州空间技术物理研究所 | Textured special-shaped structure anode on inner surface of ion thruster based on 3D additive manufacturing |
| CN112795879A (en) * | 2021-02-09 | 2021-05-14 | 兰州空间技术物理研究所 | Coating film storage structure of discharge chamber of ion thruster |
| CN116390320A (en) * | 2023-05-30 | 2023-07-04 | 安徽农业大学 | Electron cyclotron resonance discharge device and application |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1314070A (en) * | 1998-06-26 | 2001-09-19 | 汤姆森管电子有限公司 | Plasma accelerator arrangement |
| CN104653422A (en) * | 2015-01-22 | 2015-05-27 | 大连理工大学 | Three-level acceleration type spiral wave plasma propulsion device |
| US9123850B2 (en) * | 2009-11-19 | 2015-09-01 | Lockheed Martin Corporation | Systems and methods for generating electric current from hyperthermal chemical reaction |
| CN105934063A (en) * | 2016-06-02 | 2016-09-07 | 燕山大学 | Microwave ionization type plasma thruster |
| WO2016180955A2 (en) * | 2015-05-13 | 2016-11-17 | Airbus Defence And Space Limited | Charge separation mechanism |
| CN106351811A (en) * | 2016-09-09 | 2017-01-25 | 北京航空航天大学 | Low-power cylinder-type electromagnetic plasma thruster with adjustable magnetic field |
-
2017
- 2017-04-27 CN CN201710285710.7A patent/CN106968906A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1314070A (en) * | 1998-06-26 | 2001-09-19 | 汤姆森管电子有限公司 | Plasma accelerator arrangement |
| US9123850B2 (en) * | 2009-11-19 | 2015-09-01 | Lockheed Martin Corporation | Systems and methods for generating electric current from hyperthermal chemical reaction |
| CN104653422A (en) * | 2015-01-22 | 2015-05-27 | 大连理工大学 | Three-level acceleration type spiral wave plasma propulsion device |
| WO2016180955A2 (en) * | 2015-05-13 | 2016-11-17 | Airbus Defence And Space Limited | Charge separation mechanism |
| CN105934063A (en) * | 2016-06-02 | 2016-09-07 | 燕山大学 | Microwave ionization type plasma thruster |
| CN106351811A (en) * | 2016-09-09 | 2017-01-25 | 北京航空航天大学 | Low-power cylinder-type electromagnetic plasma thruster with adjustable magnetic field |
Non-Patent Citations (4)
| Title |
|---|
| 杨涓等: "电子回旋共振离子推力器放电室等离子体静电探针诊断", 《机械科学与技术》 * |
| 杨涓等: "电子回旋共振离子推进器放电室等离子体数值模拟", 《物理学报》 * |
| 杨铁链等: "电子回旋共振推力器放电室内磁场与微波电磁场分析", 《中国空间科学技术》 * |
| 毛根旺等: "《航天器推进系统及其应用》", 31 October 2009, 西北工业大学出版社 * |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107559164A (en) * | 2017-08-25 | 2018-01-09 | 上海航天控制技术研究所 | A kind of change propulsive microwave ECR propulsion system and method |
| CN109681399A (en) * | 2018-12-12 | 2019-04-26 | 上海航天控制技术研究所 | A kind of minor diameter efficient microwave ECR averager |
| CN111456921A (en) * | 2019-01-22 | 2020-07-28 | 哈尔滨工业大学 | Microwave enhancement-based field emission thruster |
| CN111456921B (en) * | 2019-01-22 | 2021-10-15 | 哈尔滨工业大学 | Colloid thruster based on microwave enhancement |
| CN110145446A (en) * | 2019-06-13 | 2019-08-20 | 哈尔滨工业大学 | A kind of micro- ox propulsion device of pulse electrical excitation |
| CN110145446B (en) * | 2019-06-13 | 2020-05-12 | 哈尔滨工业大学 | Pulse electrically-excited micro-cow propulsion device |
| CN111306024A (en) * | 2020-02-14 | 2020-06-19 | 哈尔滨工业大学 | Microwave ion propulsion unit based on lateral wall cusped magnetic field |
| CN111706482A (en) * | 2020-06-28 | 2020-09-25 | 哈尔滨工业大学 | Ion wind thrust device cooperated with microwave |
| CN112555112A (en) * | 2020-11-06 | 2021-03-26 | 兰州空间技术物理研究所 | Textured special-shaped structure anode on inner surface of ion thruster based on 3D additive manufacturing |
| CN112555112B (en) * | 2020-11-06 | 2022-06-14 | 兰州空间技术物理研究所 | Textured special-shaped structure anode on inner surface of ion thruster based on 3D additive manufacturing |
| CN112795879A (en) * | 2021-02-09 | 2021-05-14 | 兰州空间技术物理研究所 | Coating film storage structure of discharge chamber of ion thruster |
| CN116390320A (en) * | 2023-05-30 | 2023-07-04 | 安徽农业大学 | Electron cyclotron resonance discharge device and application |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106968906A (en) | A kind of plasma propulsion device | |
| Takeiri | Negative ion source development for fusion application | |
| CN106098510B (en) | A kind of repetition downfield axial direction C-band high-power pulsed ion beams | |
| CN109786205B (en) | Electron cyclotron resonance ion source | |
| CN103956314B (en) | A kind of microwave-driven is without caesium H-ion source | |
| US20190279835A1 (en) | High reliability, long lifetime, negative ion source | |
| CN105407621B (en) | A kind of compact D D accelerators for neutron production | |
| CN103953517A (en) | Hall thruster improving device | |
| CN108915969A (en) | A kind of multi-mode helicon ion thruster | |
| WO2014114986A1 (en) | Multiphase nuclear fusion reactor | |
| CN111852802B (en) | Hall effect ring type ion thruster | |
| CN110145446A (en) | A kind of micro- ox propulsion device of pulse electrical excitation | |
| CN111852803B (en) | Mixed effect annular ion thruster based on segmented anode | |
| CN106793441A (en) | A kind of resolving power is the semielliptical type radio frequency-ion microthruster of micro-ox level | |
| EP3120373A1 (en) | Compact magnet design for high-power magnetrons | |
| US8635850B1 (en) | Ion electric propulsion unit | |
| Hosseinzadeh et al. | Numerical simulation for optimization of multipole permanent magnets of multicusp ion source | |
| RU2246035C1 (en) | Ion engine | |
| CN209087761U (en) | A kind of novel plasma cathode electronics electron gun and 3D printer | |
| Akimov et al. | High-power X-band pulse magnicon | |
| CN114738217B (en) | Cathode based on microwave discharge and hollow cathode effect | |
| Qian et al. | Two-dimensional analysis of the relativistic parapotential electron flow in a magnetically insulated transmission line oscillator (MILO) | |
| US8989334B2 (en) | Aneutronic magnetron energy generator | |
| CN213392530U (en) | Inductively coupled two-stage plasma thruster | |
| CN208441977U (en) | A kind of three-level accelerating type Plasma propulsion device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170721 |