CN106704133A - Non-trigger type vacuum arc micro thruster using gas storage electrodes - Google Patents
Non-trigger type vacuum arc micro thruster using gas storage electrodes Download PDFInfo
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- CN106704133A CN106704133A CN201710137475.9A CN201710137475A CN106704133A CN 106704133 A CN106704133 A CN 106704133A CN 201710137475 A CN201710137475 A CN 201710137475A CN 106704133 A CN106704133 A CN 106704133A
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- gas storage
- vacuum arc
- negative electrode
- insulator
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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
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02E60/16—Mechanical energy storage, e.g. flywheels or pressurised fluids
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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Plasma Technology (AREA)
Abstract
The invention discloses a non-trigger type vacuum arc micro thruster using gas storage electrodes. The non-trigger type vacuum arc micro thruster can be used for microsatellites or space vehicles. A negative electrode and a positive electrode of a vacuum arc discharge module of the thruster are the gas storage metal electrodes and achieve the dual functions of discharge electrodes and propellants. The positive electrode is arranged on the periphery of the negative electrode. The positive electrode and the negative electrode are partitioned through an insulator. The surface of the insulator is covered with a gas storage metallic film. A spring is mounted at the rear end of the negative electrode. A charge and discharge circuit of an inductive energy storage module of the thruster is composed of a power source, an inductor, an IGBT transistor, a resistor, the negative electrode of the vacuum arc discharge module and the positive electrode of the vacuum arc discharge module. The thruster is small in size, low in weight and compact in structure, has the characteristics of high specific impulse and ignition stability and long service life, and is suitable for completing the tasks such as damping compensation, track lifting, positioning maintaining, maneuvering control, posture control, formation flying, launching error correction and the like of the microsatellites.
Description
Technical field
The invention belongs to pulsed plasma and microsatellite micro-thruster field, and in particular to one kind uses gas storage electrode
Triggerless micro-vacuum arc propeller.
Background technology
Pulsed plasma thruster is the microsatellite in space（Including it is small, micro-, receive, satellite etc. skin）Pulse is provided to push away
Power, damping compensation, track lifting, position holding and excitement, gesture stability, formation for completing long-life microsatellite fly
The tasks such as row, transmission error amendment.
Existing high voltage pulse plasma propeller technology mainly uses PTFE（That is Teflon）It is to push away Deng polymer
Enter agent, usually coaxial electrode structure design or parallel-plate electrode structure design.Existing pulsed plasma thruster technology
Using the high voltage triggering and driving that are stored in electric capacity.Charging to storage capacitor generally utilizes high voltage power supply or by low tension
Low pressure is transformed into required high pressure to charge storage capacitor by source by the converter that DC- turns-DC.It is stored in capacitor
High pressure causes the plasma discharge of insulator surface, thus causes insulator（Such as PTFE）Surface heating and overheat PTFE
The high rate discharge of son and correlation PTFE plasma accompaniments.Another low voltage pulse plasma propeller is using conductive
Material is propellant, such as carbon, and surface plasma is produced by Ohmic heating, discharges the overheat carbon particle of high speed.
Vacuum Arc propeller is different at several aspects with pulsed plasma thruster technology.（1）Propellant：It is existing
Pulsed plasma thruster use surface-discharge, using insulating material fusing as propellant, while avoiding the burning of electrode
Erosion；Vacuum Arc propeller is propellant using cathode material, and it forms low-impedance plasma, and what is utilized is cathode material
Ablation.（2）Acceleration mechanism：The main acceleration mechanism of pulsed plasma is Lorentz force J × B, and Vacuum Arc propeller
Main acceleration mechanism is the barometric gradient and above-mentioned Lorentz force J × B formed by plasma diffusion.（3）Triggering
Mechanism：Pulsed plasma thruster utilizes surface-discharge, and often auxiliary is touched using an a spark plug even laser
Hair, and Vacuum Arc propeller is using through a high-voltage breakdown for minimal clearance.（4）I-E characteristic（C-V characteristic）：Put
After electricity triggering, Vacuum Arc propeller electric current in the remaining time of pulse reduces, and voltage is almost unchanged, and pulsed plasma
Propeller is just the opposite, i.e., voltage reduces, and electric current is almost unchanged.
Above-described pulsed plasma thruster technology and Vacuum Arc propeller technology, all suffer from propellant and are putting
Serious ablation in electric process, service life there are problems that very big.
The content of the invention
It is an object of the invention to provide a kind of triggerless micro-vacuum arc plasma propeller of use gas storage electrode, it is
One kind has small quality（Tens arrive several hectograms）, small size (centimetres), low-voltage（Less than 1000 volts）High specific impulse it is long-lived
The plasma propeller of life.Stable discharging can be provided under tens volts of voltage to several hectovolts, and as propellant
Electrode material meets the long life requirement of resistance to ablation.
Technical scheme is as follows：
A kind of triggerless micro-vacuum arc propeller of use gas storage electrode of the invention, is characterized in, described use gas storage
The triggerless micro-vacuum arc propeller of electrode includes vacuum arc discharge module and inductive energy storage module.Described vacuum arc discharge
Module contains anode, negative electrode, insulator, metallic film I, wire coil and spring.Described inductive energy storage module comprising resistance,
Igbt transistor, pulse switch signal, inductance and power supply.In described vacuum arc discharge module, negative electrode is located at the center of axial direction
On line, the periphery of negative electrode is provided with anode, is spaced apart by insulator between anode and negative electrode, and insulator surface covers one layer of gas storage
Metallic film I, for making anode and negative electrode be in lightly conducting state.Spring is installed in the rear end of negative electrode, by the pressure of spring
Extruding fixation is carried out to negative electrode.
Power supply and inductance connection, inductance are connected with igbt transistor, and igbt transistor is connected with resistance, and resistance connects with power supply
Connect, form a charge circuit.Inductance is connected with anode, and resistance is connected with wire coil, and one is formed by igbt transistor
Discharge loop.Pulse switch signal is connected with igbt transistor, for the control of igbt transistor.
Described anode, negative electrode uses gas storage metal electrode.Metallic film is resistance value at 1 ohm to 100 kilohms
The same material or other materials of magnitude.
The structure of described vacuum arc discharge module is respectively adopted radial concentric structure or axial annular structure setting.
In described radial concentric structure, the front end face of negative electrode is set to plane, the concave panel or taper for α at an angle
Face, the angular range of α is 1 degree ~ 180 degree.
In described axial annular structure, multiple insulators, multiple gas storage metal electrodes are set between the anode and the cathode,
Insulator alternates setting with gas storage metal electrode, and one layer of gas storage metallic film is deposited on each insulator.
The material of described insulator is using the one kind in ceramics, mica, quartz.
Gas storage metal material, such as metal hydride is used to provide electric discharge as vacuum arc discharge module logical in the present invention
The electrode material in road and the propellant material of propeller.The fuel factor that arc discharge process causes is heated to propellant material,
So that gas storage metal electrode discharges the gas of storage, the release of gas and ionization process greatly reduce the burning of propellant
Erosion, improves the service life of propellant.
Insulator surface covering gas storage metallic film in the present invention, in the propellant material as propeller and as true
Micro conductive contact is formed between the negative electrode and anode of empty arc discharging electrode, gas storage metallic film material can be with propellant material one
The gas storage metallic film of sample or other materials.After discharge pulse terminates, deposited after the cooling period as the cathode material of propellant
On the insulator, the metallic film that insulator surface ablation is consumed can be supplemented.As sparking electrode and propellant
Metal material, such as the portion gas of release with gettering ability, can carry out resorption, gas storage is formed once more by Titanium
Metal material.
The geometric electrode structure of the vacuum arc discharge module in the present invention can be radial concentric structure or axial annular knot
Structure, or traditional plate stack layered structure.Negative electrode in radial concentric design is solid gas storage metal material, external diameter
It is 2mm ~ 10mm, length is 5mm ~ 50mm；Insulator and anode are hollow design, and the internal diameter of insulator and anode is same respectively
Cathode insulation external diameter match, insulator thickness be 0.5mm ~ 2mm, length be 5mm ~ 20mm, anode thickness 2mm ~
10mm, length is in 5mm ~ 20mm.Isolator material be easy processing and can the insulating materials such as the ceramic, quartzy of surface coating, mica,
Anode is similarly gas storage metal material.Negative electrode, insulator and the anode that axial annular is designed are hollow ring design, and internal diameter is
2mm ~ 10mm, thickness is 2mm ~ 10mm, and, in 5mm ~ 20mm, the length of negative electrode is in 5mm ~ 50mm, insulator thickness for the length of anode
In 0.5mm ~ 2mm.
Using spring extruding from feed-in type assembling structure in the present invention.Squeezed using spring away from one end of electric discharge in negative electrode
The mode of pressure is assembled, when cathode material due to ablation during arc discharge after being consumed, the pressure of spring can automatically by
Negative electrode is pushed to region of discharge, forms the cathode material added machinery from feed-in.
The enhanced vacuum arc discharge module of magnetic is used in the present invention.Put by Vacuum Arc by the coil of copper wire coiling in magnetic field
Formed during electric current.Brass wire diameter is pricked number and is pricked tens to hundreds of in submillimeter magnitude, and the magnetic field intensity of formation is in tens Gausses
To hundreds of Gausses.The presence in magnetic field, further enhancing focusing and the accelerating jetting effect of discharge plasma plume, improve
The service efficiency of propellant, has widened the thrust range of propeller.
Using inductive energy storage to vacuum arc discharge module for power supply in the present invention.Ensure small size using solid switch and carry
For power parameter wider：Electric current is arrived in several volts to kilovolt magnitude, pulse width in milliampere to hundred order of amps, voltage in nanosecond
Millisecond magnitude.Additionally, being also operable with DC mode.
The plasma jet for being used to provide thrust in the present invention is produced by vacuum arc discharge, for forming Vacuum Arc
Cathode and anode electrode is separated by insulator, and vacuum arc discharge can stabilization formation at tens volts.Specific work process is：Work as IGBT
When transistor switch is opened, inductance is charged by a dc source of 10V -50V；After switch is shut, accumulate in inductance
Energy is applied on negative electrode and anode, and crest voltage is produced between two electrodesLdI/dt, reach several hectovolts.Electric current is in insulation
Sublist face micro conductive layer and negative electrode between micro- contact point aggregation, due to joule heating effect produce blast plasma, wait from
Daughter rapidly diffuses into the gap between negative electrode and anode, forms vacuum arc discharge.Electric discharge near cathode surface negative electrode spot etc.
Gas ions are sprayed from negative electrode to perpendicular to the direction of cathode surface.Discharge current flows through coil and produces pulsed magnetic field, further right
The injection of plasma plume is focused and accelerates, and improves the performance of propeller.
The external operating environment that the triggerless micro-vacuum arc propeller of gas storage electrode is used in the present invention is vacuum or big
Compression ring border.
The beneficial effect of the triggerless micro-vacuum arc propeller of use gas storage electrode of the invention is, can be at tens volts
Stable discharging is provided under to the voltage of several hectovolts, can further reduce the size of single Vacuum Arc propeller, and conduct is pushed away
The electrode material for entering agent meets the long life requirement of resistance to ablation.The present invention passes through using the setting of array, by multiple Vacuum Arcs
Discharge module is used in combination, and improves the job stability of propeller, widens the thrust range of propeller.
Brief description of the drawings
Fig. 1 is a kind of structural representation of the triggerless micro-vacuum arc propeller of use gas storage electrode of the invention；
Fig. 2 is the radial concentric structural representation of the vacuum arc discharge module in the present invention, wherein Fig. 2（a）Negative electrode end face be
Plane, Fig. 2（b）Negative electrode end face be spill or conical surface with certain angle；
Fig. 3 is the axial annular structural representation of the vacuum arc discharge module in the present invention, wherein Fig. 3（a）It is single insulator knot
Structure, Fig. 3（b）It is many insulator structures；
In figure, the 1. resistance of 2. negative electrode of anode, 3. insulator I, 4. metallic film I, 5. wire coils, 6. spring 7.
The metallic films of 12. insulator II of 8.IGBT transistors 9. pulse switch signal, 10. inductance, 11. dc source 13.
The gold medals of 18. insulator IV of II 14. virtual anode I, 15. insulator III, 16. metallic film III, 17. virtual anode II 19.
The virtual anode III of category film IV 20..
Specific embodiment
Describe the present invention in detail with reference to the accompanying drawings and examples.
Embodiment 1
Fig. 1 is a kind of structural representation of the triggerless micro-vacuum arc propeller of use gas storage electrode of the invention.Fig. 2 is this
The radial concentric structural representation of the vacuum arc discharge module in invention, wherein Fig. 2（a）Negative electrode end face be plane, Fig. 2（b）
Negative electrode end face be spill or conical surface with certain angle.Fig. 3 is the axial direction of the vacuum arc discharge module in the present invention
Loop configuration schematic diagram, wherein Fig. 3（a）It is single insulator structure, Fig. 3（b）It is many insulator structures.In Fig. 1 ~ Fig. 3, this hair
A kind of triggerless micro-vacuum arc propeller of bright use gas storage electrode, including vacuum arc discharge module and inductive energy storage mould
Block.Described vacuum arc discharge module contains anode 1, negative electrode 2, insulator 3, metallic film I4, wire coil 5 and spring 6.Institute
The inductive energy storage module stated includes resistance 7, igbt transistor 8, pulse switch signal 9, inductance 10 and power supply 11.Described vacuum
In arc discharge module, negative electrode 2 is located on the center line of axial direction, and the periphery of negative electrode 2 is provided with anode 1, between anode 1 and negative electrode 2
It is spaced apart by insulator 3, the surface of insulator 3 covers one layer of metallic film I 4 of gas storage, it is micro- for being in anode 1 and negative electrode 2
Conducting state.Spring 6 is installed in the rear end of negative electrode 2, by the pressure fixing negative electrode 2 of spring 6.
Power supply 11 is connected with inductance 10, and inductance 10 is connected with igbt transistor 8, and igbt transistor 8 is connected with resistance 7, electricity
Resistance 7 is connected with power supply 11, forms a charge circuit.Inductance 10 is connected with anode 1, and resistance 7 is connected with wire coil 5, passes through
Igbt transistor 8 forms a discharge loop.Pulse switch signal 9 is connected with igbt transistor 8, for igbt transistor 8
Control.
Described anode 1, negative electrode 2 uses gas storage metal electrode；Metallic film I 4 uses gas storage metallic film.
In the present embodiment, the structure of described vacuum arc discharge module uses radial concentric structure setting, the front end of negative electrode 2
Face is set to plane, such as Fig. 2（a）It is shown.Described anode 1 and negative electrode 2 are the titantium hydride TiH of gas storage1.5Material, insulator 3 is
The alumina ceramic material of high temperature sintering, is 5 microns of metal titanium membranes of thickness in the metallic film I 4 of the end face of region of discharge, and
Carry out being flushed with hydrogen treatment, the atomic ratio of hydrogen is similarly 1.5.Negative electrode 2 is solid construction, external diameter 5mm, length 20mm；Insulator 3 and sun
Pole 1 is hollow cylinder, insulator 3 internal diameter 5mm, external diameter 7mm, length 10mm；Anode 1 internal diameter 7mm, external diameter 10mm.Negative electrode 2
And the resistance between anode 1 is 5 ohm.Wire coil 5 is formed by the 100 copper wire coilings for pricking a diameter of 0.5mm.Inductive energy storage mould
The power supply 11 of block provides the voltage output of 10 ~ 100V, and inductance 10 is 100mH, and resistance 7 is 0.5 ohm, and igbt transistor 8 is
IRG4PH50UD, pulse switch signal 9 is produced by TC4420CPA.When pulse switch signal 9 is opened, inductance 10 is by power supply 11
Charge, when pulse switch signal 9 is closed, energy of the accumulation in inductance 10 is applied on anode 1 and negative electrode 2, electrode it
Between produce crest voltageLdI/dt.Gather micro- contact position of the electric current between the metallic film I 4 and negative electrode 2 of alumina ceramic face
Collection, with the increase of electric current, joule heating effect causes that the temperature and ratio resistance of contact position increase sharply, and local power density is fast
Speed increases, and when temperature is more than 200 DEG C, the hydrogen release in negative electrode 2 and metallic film I 4 is released, and is produced in micro- contact position initial etc.
Gas ions, and then cause vacuum breakdown, form the injection of arc plasma plume.During this, electric current is dropped rapidly to zero,
Voltage keeps constant in 30V.During the current metal coil 5, the magnetic field of 200 Gausses, further plasma are axially being produced
Plume enters row constraint and acceleration, produces the thrust of several micro- oxen.The propeller is 100 microseconds in the duration of individual pulse, can
The working life of more than 1000s is provided.
The external operating environment of the described triggerless micro-vacuum arc propeller for using gas storage electrode is vacuum or air
Environment.
Embodiment 2
The present embodiment is identical with the overall structure of embodiment 1, is a difference in that, the front end face of negative electrode 2 is set at an angle be α
Concave panel, the angle of α is 90 degree, such as Fig. 2（b）It is shown.The material of described insulator is using ceramics.
Embodiment 3
The present embodiment is identical with the overall structure of embodiment 1, is a difference in that, the structure of described vacuum arc discharge module is used
Axial annular structure setting, such as Fig. 3（a）It is shown.The material of described insulator uses mica.Anode 1, negative electrode 2 and insulator 3
Hollow ring structure is, internal diameter is 5mm, and thickness is 5mm, and the length of anode 1 is 20mm, and the length of negative electrode 2 is 40mm, insulator
Length be 1mm.The metallic film I 4 of the bore area of insulator 3 is 5 microns of metal titanium membranes of thickness, and carries out being flushed with hydrogen treatment, hydrogen
Atomic ratio be 1.5.
Embodiment 4
The present embodiment is identical with the overall structure of embodiment 3, is a difference in that, described vacuum arc discharge module uses axial rings
The laminated construction of shape is set, insulator II 12, insulator III 15, the insulator IV 18 for setting in the present embodiment, empty sun
Pole I1 4, virtual anode II 17, virtual anode III 20, metallic film II 13, metallic film III 16, metallic film IV 19, such as
Fig. 3（b）It is shown.Virtual anode I 14, virtual anode is spaced using insulator III 15, insulator IV 18 between anode 1 and negative electrode 2
II 17, virtual anode III 20, deposit 1 micron of metallic film II of thickness respectively on insulator III 15, insulator IV 18
13rd, metallic film III 16.The material of described insulator uses mica.
Finally it should be noted that above specific embodiment is merely illustrative of the technical solution of the present invention and unrestricted, to the greatest extent
Pipe has been described in detail with reference to preferred embodiment to the present invention, it will be understood by those within the art that, can be to this
The technical scheme of invention is modified or equivalent, and without deviating from the spirit and scope of technical solution of the present invention, it all should
Cover in the middle of scope of the presently claimed invention.
Claims (7)
1. the triggerless micro-vacuum arc propeller of a kind of use gas storage electrode, it is characterised in that：Described use gas storage electrode
Triggerless micro-vacuum arc propeller include vacuum arc discharge module and inductive energy storage module；Described vacuum arc discharge module
Contain anode（1）, negative electrode（2）, insulator（3）, metallic film I（4）, wire coil（5）And spring（6）；Described inductance storage
Energy module includes resistance（7）, igbt transistor（8）, pulse switch signal（9）, inductance（10）And power supply（11）；Described vacuum
In arc discharge module, negative electrode（2）On the center line of axial direction, negative electrode（2）Periphery be provided with anode（1）, anode（1）With the moon
Pole（2）Between pass through insulator（3）It is spaced apart, insulator（3）Surface covers one layer of metallic film I of gas storage（4）, for making sun
Pole（1）With negative electrode（2）In lightly conducting state；Negative electrode（2）Rear end install spring（6）, by spring（6）Pressure to negative electrode
（2）Carry out extruding fixation；
Power supply in described inductive energy storage module（11）With inductance（10）Connection, inductance（10）With igbt transistor（8）Connection,
Igbt transistor（8）With resistance（7）Connection, resistance（7）With power supply（11）Connection, forms a charge circuit；Inductance（10）With
Anode（1）Connection, resistance（7）With wire coil（5）Connection, by igbt transistor（8）Form a discharge loop；Pulse is opened
OFF signal（9）With igbt transistor（8）Connection, for igbt transistor（8）Control.
2. the triggerless micro-vacuum arc propeller of use gas storage motor according to claim 1, it is characterised in that：It is described
Anode（1）, negative electrode（2）Use gas storage metal electrode；Metallic film I（4）Using gas storage metallic film.
3. the triggerless micro-vacuum arc propeller of use gas storage electrode according to claim 1, it is characterised in that described
Vacuum arc discharge module use radial concentric structure or axial annular structure setting.
4. the triggerless micro-vacuum arc propeller of use gas storage motor according to claim 3, it is characterised in that：It is described
Radial concentric structure in, negative electrode（2）Front end face be set to plane, it is at an angle be the concave panel or taper surface of α.
5. the triggerless micro-vacuum arc propeller of use gas storage motor according to claim 3, it is characterised in that：It is described
Axial annular structure in, in anode（1）With negative electrode（2）Between multiple insulators, multiple gas storage metal electrodes, insulator are set
Setting is alternated with gas storage metal electrode.
6. according to claim 1 or 5 using the triggerless micro-vacuum arc propeller of gas storage motor, it is characterised in that：
One layer of gas storage metallic film is deposited on each described insulator.
7. the triggerless micro-vacuum arc propeller of use gas storage motor according to claim 1, it is characterised in that：It is described
Insulator material using ceramics, mica, it is quartzy in one kind.
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| CN108194295A (en) * | 2017-12-28 | 2018-06-22 | 西安航天动力研究所 | A kind of triggerless electrode that can reduce vacuum arc thruster starting the arc energy |
| CN110159501A (en) * | 2019-06-28 | 2019-08-23 | 中国人民解放军国防科技大学 | Ultra-low rail variable thrust air suction type magnetic plasma thruster |
| CN110486243A (en) * | 2019-09-11 | 2019-11-22 | 哈尔滨工业大学 | A kind of micro cathode electric arc propulsion system |
| CN111486070A (en) * | 2020-04-16 | 2020-08-04 | 哈尔滨工业大学 | Micro-cathode arc thrust system based on accelerating electrode |
| WO2021057892A1 (en) * | 2019-09-25 | 2021-04-01 | 国防科技大学 | Inductive plasma acceleration apparatus and method |
| CN113716074A (en) * | 2021-11-04 | 2021-11-30 | 北京理工大学 | Satellite with electric propulsion system |
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