CN107091210B - A kind of pulsed plasma thruster based on capillary discharging - Google Patents
A kind of pulsed plasma thruster based on capillary discharging Download PDFInfo
- Publication number
- CN107091210B CN107091210B CN201710351905.7A CN201710351905A CN107091210B CN 107091210 B CN107091210 B CN 107091210B CN 201710351905 A CN201710351905 A CN 201710351905A CN 107091210 B CN107091210 B CN 107091210B
- Authority
- CN
- China
- Prior art keywords
- thruster
- working medium
- plasma
- propellant
- circuit
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H1/00—Using plasma to produce a reactive propulsive thrust
- F03H1/0093—Electro-thermal plasma thrusters, i.e. thrusters heating the particles in a plasma
-
- 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
- F03H1/0006—Details applicable to different types of plasma thrusters
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01T—SPARK GAPS; OVERVOLTAGE ARRESTERS USING SPARK GAPS; SPARKING PLUGS; CORONA DEVICES; GENERATING IONS TO BE INTRODUCED INTO NON-ENCLOSED GASES
- H01T13/00—Sparking plugs
- H01T13/20—Sparking plugs characterised by features of the electrodes or insulation
- H01T13/39—Selection of materials for electrodes
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01T—SPARK GAPS; OVERVOLTAGE ARRESTERS USING SPARK GAPS; SPARKING PLUGS; CORONA DEVICES; GENERATING IONS TO BE INTRODUCED INTO NON-ENCLOSED GASES
- H01T13/00—Sparking plugs
- H01T13/52—Sparking plugs characterised by a discharge along a surface
Landscapes
- Engineering & Computer Science (AREA)
- 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
This disclosure relates to a kind of pulsed plasma thruster based on capillary discharging, including power supply processing unit, main capacitance, semiconductor spark plug, firing circuit, main discharge circuit, propellant working medium, cathode nozzle, anode and organic glass shell.The disclosure keeps main discharge current and plasma motion direction at an angle, electromagnetism is introduced under the action of self-induction magnetic field and is accelerated by introducing cathode nozzle.Different from traditional electromagnetism accelerating type pulsed plasma thruster, the disclosure makes full use of electric heating acceleration mechanism, improves the energy utilization efficiency of pulsed plasma thruster, under lower power levels, system overall efficiency can be improved, be more suitable for microsatellite low power applications occasion.
Description
Technical field
The disclosure belongs to Pulse Power Techniques and field of power machinery technology, is related to a kind of pulse based on capillary discharging
Plasma thruster.
Background technique
1, traditional cold air promotes and chemical propulsion system is needed using propellant receptacle cryopreservation device and supply system, so that dress
It is big to set total quality, structure is complicated.Above two propulsion system specific impulse is small simultaneously, low efficiency, largely limit its
The space application of microsatellite.Pulsed plasma thruster is applied to Zond 2 for the first time from the sixties in the last century former Soviet Union
Since aircraft, as a kind of novel electric propulsion system, pulsed plasma thruster has obtained significant progress.And with
The expansion of microsatellite application market, pulsed plasma thruster relies on it than leaping high, quality is small, structure is simple, research and development are all
Phase is short, can provide the advantages such as small controllable thrust, executes in high-precision task and is with a wide range of applications in microsatellite.
2, traditional pulsed plasma thruster uses electromagnetism acceleration mechanism, connects energy storage by two parallel electrode plates
Capacitor, propellant working medium are placed among two-plate.Under initial energy storage state, introduced initially by modes such as spark plug triggerings
Charged particle lures that in propellant surface creeping discharge occurs for capacitor into, and the electric current ablation that arc discharge generates simultaneously dissociates working medium shape
At plasma, and is accelerated to spray outward by the effect of Lorentz force in self-induction magnetic field and generate thrust.
Although 3, electromagnetic type pulsed plasma thruster uses solid propellant, by propellant working medium and thruster sheet
Body combines to form modular unit, but since electromagnetic force can only accelerate charged particle, little for neutral molecule acceleration effect.It is real
It tests and shows neutral molecule quality caused by ablation accounts for total ablation resultant quality 70%~90%, so that pulsed plasma
The acceleration efficiency of thruster is low and influences thruster integral energy transformation efficiency.Simultaneously because lag ablation phenomen and corpuscular emission
The presence of effect, so that the utilization rate of working medium is lower, there are still very in the extensive use on the microsatellite of small-power level
Big obstruction.
Summary of the invention
Based on this, the invention discloses a kind of pulsed plasma thruster based on capillary discharging,
The thruster includes: power supply processing unit, semiconductor spark plug, firing circuit, main discharge circuit and propellant
Working medium；
The power supply processing unit is used to be supplied to the required voltage of thruster work, to the main capacitance in main discharge circuit
It carries out charging and powers to firing circuit；
The firing circuit makes semiconductor spark plug that creeping discharge generation initial strip electrochondria occur for exporting high voltage pulse
Son；
The initial charged particles that the semiconductor spark plug generates enter in propellant working medium, pass through continuous ionization by collision
Generate plasma；
The propellant working medium is capillary type, and with the generation of plasma, propellant working medium surface occurs to dodge along face
Network forms the electric discharge of main capacitance in main discharge circuit；
The main discharge circuit for the electric energy that power supply processing unit provides is stored and is transmitted, ablation propellant work
Matter simultaneously accelerates plasma, main capacitance energy is converted to plasma kinetic energy, to form plasma jet, generation is pushed away
Power.
Compared with prior art, the advantageous effects that the disclosure has:
1, the novel pulse plasma thruster provided by the invention based on capillary discharging, accelerated using electrothermal forces etc.
The mechanism of gas ions is realized different from traditional electromagnetism acceleration mechanism to the neutrality point for accounting for the ablation resultant quality overwhelming majority
The abundant acceleration of son；Plasma arc of the present invention road energy deposition efficiency reaches 50% or more, and it is whole to be conducive to raising thruster
Body energy utilization efficiency.
2, the present invention uses high-performance semiconductor spark plug, creeping discharge can occur under lower DC voltage and generate
Charged particle, insulation system are simplified, and the overall security and reliability of firing circuit improve；It is controlled using semiconductor switch
Firing circuit can reach the adjustable purpose of thruster power consumption, thrust and momentum with accuracy controlling working frequency.
3, the present invention realizes the modular combination of propellant working medium Yu thruster ontology, and structure is simple, and movable part is few,
High reliablity.Keep thruster overall device dimensions smaller using coaxial configuration design, it is easy for installation.It can be under same external structure
Facilitate the size for adjusting propellant working medium, meets the requirement of different performance output parameter.
4, the present invention uses divergent nozzle, introduces electromagnetism acceleration mechanism while increasing plasma jet angle, into
One step improves particle exit velocities, improves thrust efficiency and obtains high specific impulse.
Detailed description of the invention
Fig. 1 is the pulsed plasma thruster work implementation schematic diagram based on capillary discharging；
Fig. 2 is the typical discharges waveform of the pulsed plasma thruster based on capillary discharging；
As shown in the figure: 1 is cathode nozzle；2 be spark plug tungsten electrode；3 be cathode connection bolt；4 be spark plug semiconductor
Layer；5 be propellant working medium；6 be organic glass shell；7 be anode；8 be anode connection bolt；9 be main discharge capacity；10 be mould
Quasi- vacuum environment；11 be power supply processing unit；12 be firing circuit.
Specific embodiment
It elaborates with reference to the accompanying drawing to the embodiment of the present invention:
In one embodiment, the invention discloses a kind of pulsed plasma thruster based on capillary discharging,
The thruster includes: power supply processing unit, semiconductor spark plug, firing circuit, main discharge circuit and propellant
Working medium；
The power supply processing unit is used to be supplied to the required voltage of thruster work, to the main capacitance in main discharge circuit
It carries out charging and powers to firing circuit；
The firing circuit makes semiconductor spark plug that creeping discharge generation initial strip electrochondria occur for exporting high voltage pulse
Son；
The initial charged particles that the semiconductor spark plug generates enter in propellant working medium, pass through continuous ionization by collision
Generate plasma；
The propellant working medium is capillary type, and with the generation of plasma, propellant working medium surface occurs to dodge along face
Network forms the electric discharge of main capacitance in main discharge circuit；
The main discharge circuit for the electric energy that power supply processing unit provides is stored and is transmitted, ablation propellant work
Matter simultaneously accelerates plasma, main capacitance energy is converted to plasma kinetic energy, to form plasma jet, generation is pushed away
Power.
More preferably, the thruster further include: cathode nozzle, anode and organic glass shell；
The cathode nozzle is for accelerating plasma；
The organic glass shell is for connecting cathode nozzle, anode and propellant working medium.
In the present embodiment, low for existing electromagnetism accelerating type pulsed plasma thruster heavy particle acceleration efficiency, energy
The problems such as measuring transformation efficiency low (5%~10%), structure is simple, and repeated work consistency is good and has both high specific impulse parameter and height pushes away
The pulsed plasma thruster based on capillary discharging of force efficiency.The present embodiment generates relative low temperature by capillary discharging
And high-density plasma, it is poor to make to be formed immense pressure between working medium inside cavity and extraneous vacuum environment, obtains plasma
Sufficient electric heating accelerates, and improves the performance of pulsed plasma thruster.
The present embodiment is achieved through the following technical solutions:
A kind of novel pulse plasma thruster based on capillary discharging, the present invention include: power supply processing unit, master
Capacitor, semiconductor spark plug, firing circuit, main discharge circuit, propellant working medium, cathode nozzle, anode and organic glass shell.
Wherein: propellant working medium is in capillary, cathode nozzle and anode distribution in working medium cavity both ends, and is had by screw thread and outside
The connection of machine glass shell, package unit is coaxial configuration；High-performance semiconductor spark plug is mounted on cathode nozzle, firing circuit
Output high direct voltage makes spark-discharge generate initial plasma.Power supply processing unit is main capacitor charging by transmission line,
Capacitor both ends are connected to anode and cathode by transmission line, constitute main discharge circuit, and bulk loop is very compact, to reduce circuit electricity
Sense increases electric heating acceleration efficiency.
In one embodiment, the firing circuit includes: ignition capacitor, isolation kenetron, ignition switch
With pre-trigger circuit；
The ignition capacitor high-voltage end is connect by isolation kenetron with ignition switch one end, low-pressure end with push away
Power device cathode nozzle is connected；
The pre-trigger circuit output pulse signal drive ignition switch makes ignition capacitor discharge to semiconductor spark plug
Generate initial charged particles.
In the present embodiment, heretofore described firing circuit includes ignition capacitor, isolation kenetron, igniting
Switch and corresponding pre-trigger circuit.The capacity of ignition capacitor is 0.1 μ F, and DC Module passes through charging resistor for Ignition capacitor
Device charges to 600V~1000V, and ignition capacitor high-voltage end is connect by isolation kenetron with ignition switch one end, low
Pressure side connects thruster cathode nozzle.Pre-trigger circuit output pulse signal drive ignition switch puts ignition capacitor to spark plug
Electricity generates initial charged particles.Isolation kenetron is avoided for main discharge circuit and ignition circuit to be isolated because master is put
Electric current causes energy deposition efficiency in plasma arcs road to reduce to the shunting of firing circuit.
Semiconductor spark plug is induced by the pulse voltage that firing circuit exports 600V~1000V first to occur to put along face
Electricity generates partially charged particle.Enter in capillary cavity body under the action of electric field force and collide with working medium surface, passes through
Ionization by collision generates more charged particles.The increasing of number of charged particles causes capillary interior insulation level to decline, and with etc. from
The formation in daughter area, main capacitance, cathode nozzle, anode and capillary cavity body form discharge channel, and main discharge is formed.Main discharge
High current sedimentary energy in plasma channel generates amount of heat and ablation capillary wall, and capillary wall is to electric arc
On the one hand effect of contraction keeps electric arc cooling by ablation effect, on the other hand polytetrafluoroethylene (PTFE) molecule can be made to be adequately ionized, and generates
More multiparticle.Capillary cavity is full of by high temperature and pressure plasma rapidly, propellant surface immense pressure effect under, wait from
Daughter, which is fully accelerated to spray outward, forms jet stream generation thrust.
In one embodiment, the propellant working medium uses solid polytetrafluor ethylene material；
The propellant working medium is coaxial capillary type, the output parameter according to required for the space tasks of thruster
Change the length and internal diameter of working medium；
The capillary working medium bore is 1mm~10mm, and length is 9mm~20mm.
In the present embodiment, the propellant working medium uses solid polytetrafluor ethylene material, without complicated stowage arrangement
And supply system, it can be in long term storage under space environment.The present embodiment proposes a kind of new propellant working medium structure, i.e., coaxially
Capillary type, the length and internal diameter of output parameter change working medium that can be as needed, eliminates conventional propellant supply system kind
Required constant force spring simplifies working substance supply mode.Capillary cavity can constrain electric arc simultaneously, and electrical discharge arc can
Uniform ablation working medium surface decomposes working medium ionization more abundant, can in nominal operation number can steady operation, and export
Parameter can keep relative stability.The propellant working medium of capillary type can further constrain particle caused by lag ablation in vacuum
In cannot free loss, so that it is depended on working medium or electrode surface, can in next discharge process it is accelerated after spray, it is suppressed that
Corpuscular emission effect.
In one embodiment, the pre-trigger circuit includes capacitor group, semiconductor switch, control circuit, protection two
Pole pipe and pulse transformer；
The control circuit is for being connected semiconductor switch；
Primary side of the capacitor group for pulse transformer is discharged, and high in the output pulse of pulse transformer pair side
Pressure, is applied in the filp-flop stage and low-pressure end of ignition switch and switches it on.
In the present embodiment, the pre-trigger circuit include capacitor group, semiconductor switch and corresponding control circuit,
Protection diode and pulse transformer.Wherein capacitor group is in parallel using the capacitor of two 1.0 μ F, and charging voltage is 0~200V.
After making semiconductor switch conducts by control circuit, the electric discharge of capacitor pulse transformer primary side, and on pulse transformer pair side
High voltage pulse is exported, is applied in the filp-flop stage and low-pressure end of ignition switch and switches it on.Pass through adjusting control circuit conducting half
The working frequency of pulsed plasma thruster is adjusted in the frequency of conductor switch, makes its highest can be under the repetition rate of 1Hz
Work, and output performance consistency is good.
In one embodiment, the material of the semiconductor spark plug semiconductor is using silicon carbide as substrate, by zirconium dioxide,
Aluminum oxide and glass are formed with certain proportion and silicon carbide mixed sintering, the porosity 5%, water absorption rate 0.8%.
In the present embodiment, the material of the semiconductor spark plug is using silicon carbide as substrate, by zirconium dioxide, three oxidations two
Aluminium and glass are formed with certain proportion and silicon carbide mixed sintering, the porosity 5%, and water absorption rate 0.8% can be effectively improved fire
The carbon deposition phenomenon on the surface Hua Sai increases the service life of thruster.It can occur to dodge along face under the DC voltage of 600V in vacuum
Network discharges charged particle.
In one embodiment, the cathode nozzle be divergent nozzle shape, cathode nozzle half angle angle be 15 °~
30 °, length is 10mm~25mm；
Screw assembly is used between the cathode nozzle and organic glass shell and is fitted close.
In one embodiment, the anode is hollow cylinder shape, and spiral shell is used between the anode and organic glass shell
Line assembly, and there are the allowances of 0.8-1.2mm to guarantee the cooperation between propellant working medium.
In the present embodiment, the cathode nozzle and anode are arranged using coaxial configuration, anode be equipped with external screw thread with it is organic
Glass shell connection, can adjust propellant working medium length more conveniently.Cathode is set as divergent nozzle shape, passes through internal screw thread
With organic glass cage connection.Cathode nozzle half angle is 15 °~30 °, and length is 10mm~25mm.Had using divergent nozzle
Conducive to plasma jet angle is increased, the electric heating acceleration efficiency of pulsed plasma thruster is improved.Simultaneously as the angle of flare
Presence, keep main discharge current and plasma motion direction at an angle, due to the presence in self-induction magnetic field, it will introduce
Electromagnetism acceleration mechanism accelerates plasma in the axial direction using Lorentz force, improves energy conversion efficiency and specific impulse.
In one embodiment, the thruster is worked with impulse form, and when work, consumed energy was held by main capacitance
Amount and charging voltage control, working frequency are 0~1Hz, and pulse working time is 4~5 μ s.
In one embodiment, the main capacitance capacity is the 1 μ F of μ F~4.5, and charging voltage is 1kV~3kV, primary power
For 0.5J~20.25J.
In the present embodiment, the main capacitance both ends respectively with the anode and cathode nozzle phase of pulsed plasma thruster
Even.The capacity of main capacitor is the 1 μ F of μ F~4.5, and charging voltage is 1kV~3kV, and primary power is 0.5J~20.25J.
In one embodiment, referring to Fig.1, the present invention, which discloses, provides a kind of pulsed plasma based on capillary discharging
Thruster, this example include cathode nozzle 1, spark plug tungsten electrode 2, cathode connection bolt 3, spark plug semiconductor layer 4, propellant
Working medium 5, organic glass shell 6, anode 7, anode connection bolt 8, main discharge capacitor 9, vacuum cavity 10, power supply processing unit 11
With firing circuit 12.Thruster outer diameter is 24mm in the present invention, and total length is 43mm~54mm
As shown in Figure 1, the present invention is placed in vacuum cavity 10 according to actual working environment needs, it is possible to provide vacuum degree 5
×10- 3Pa vacuum environment below.The present invention charges to volume to main discharge capacitor 9 at work, by power supply processing unit 11
Constant voltage.After firing command arrival, after one direct current of application of firing circuit 12 is pressed on tungsten electrode 2, in spark plug semiconductor layer 4
Upper generation creeping discharge, the initial charged particles of generation enter under the action of anode 7 and cathode nozzle 1 are formed by electric field to be pushed away
Into in agent working medium 5, plasma is generated by continuous ionization by collision, with the decline of channel internal impedance, 5 table of propellant working medium
The electric discharge that edge flashing forms main capacitance 9 occurs for face, forms plasma jet under the effect of dozens of atmospheric pressure and generates thrust.
The firing circuit 12 makes spark plug semiconductor layer 4 that edge flashing occur to provide ignition energy, specific to wrap
Ignition capacitor, isolation kenetron, gas switch and corresponding pre-trigger circuit are included.The wherein appearance of ignition capacitor
Amount is 0.1 μ F, and charging voltage is 600V~1000V.Igniting is controlled according to the turn-on frequency of semiconductor switch in pre-trigger circuit
The discharge frequency of capacitor, and then control the working frequency of thruster.For the consistency for guaranteeing thruster output parameter, igniting frequency
Rate is up to 1Hz.
The main capacitance 9 uses low equivalent series resistance capacitor, to reduce during discharge due to capacitor internal driving
Caused by energy loss.9 capacity of main capacitance is the 1 μ F of μ F~4.5 in the present invention, and charging voltage is 1kV~3kV, can be according to work
Frequency is set in the range, and primary power is 0.5J~20.25J.
The cathode 1 uses brass material as grounding electrode, is designed as divergent nozzle, and half angle is 15 °~
30 °, length is 10mm~25mm.On the one hand guarantee that stablizing for electric discharge occurs as electrode composition discharge loop, on the other hand make
For nozzle guide plasma jet direction, introduces electromagnetism acceleration mechanism and increase specific impulse and improve thruster whole efficiency.
The high performance spark plug 4 is mounted on cathode nozzle at plasma exit, is used as spark using tungsten electrode 2
The high-voltage end of plug, has biggish electron emission coefficiency and ablation resistance is good.It is low as spark plug using the cathode 1 of thruster
Pressure side can avoid complicated insulation system setting while reduction device volume.
Further, the spark plug semiconductor layer 4 is using silicon carbide as substrate, mix in certain proportion zirconium dioxide,
Aluminum oxide and glass have lower water absorption rate and air-breathing rate, improve conventional ignition plug to a certain extent because of surface area
Carbon and the problem of fail, increase the service life of thruster.Meanwhile it can occur under the DC voltage of 600V along face in vacuum
Electric discharge generates initial charged particles and stablizes triggering thruster work, greatly reduces the requirement of dielectric level, it is whole to simplify device
Body structure.
The cathode connection bolt 3 and anode connection bolt 8 can be such that transmission line connect with electrode seal, reduce electrode and pass
Contact resistance between defeated line keeps circuit more compact to improve energy utilization efficiency.
The propellant working medium 5 uses solid polytetrafluor ethylene material, is designed as coaxial capillary and is mounted on 7 He of anode
Between cathode nozzle 1, propellant working medium feeding mechanism is eliminated, compared with traditional pulsed plasma thruster, in electric discharge electricity
Under arc effect, promote the ionization rate of agent molecule higher.Use polytetrafluoroethylene (PTFE) as the thruster of propellant working medium, compared to it
His gas exhausted material can generate bigger specific impulse and first momentum, and surface Non-carbonized under given sedimentary energy, can be improved and push away
The service life of power device.Propellant working medium 5 can change structural parameters according to actual needs in the present invention.5 caliber of propellant working medium
For 1mm~10mm, length is 9mm~20mm.
The fixed device of the propeller uses organic glass shell 6, is connected through a screw thread cathode nozzle 1 and anode 7, realizes
The close connection of thruster main body, the stability with reliability.
The anode 7 uses brass material as high-field electrode, is designed as hollow circuit cylinder figure, it is whole can to effectively reduce device
Weight.Electrode end surface and propulsion caused by huge pressure inside plasma when to avoid because of machining accuracy or thruster operation
5 end face of agent working medium contacts not close situation, using Screw assembly and there are certain abundant between anode 7 and organic glass shell 6
Amount, and different capillary pipe lengths can be adapted to from the connection length of organic glass shell 6 to reach and be fitted close by adjusting.
The power supply processing unit 11 is converted to satellite platform busbar voltage (generally 28V) needed for thruster work
Voltage is simultaneously monitored.Power supply processing unit shares the output of three tunnels in the present invention, is respectively converted to the satellite busbar voltage of 28V
Main capacitance 9 charges required 1kV~3kV, 0~200V needed for the charging of capacitor group, firing circuit midpoint in pre-trigger circuit
600V~1000V needed for thermoelectricity condenser charge.
Further, power supply processing unit connects main capacitance and Ignition capacitor by hv transmission line.Power supply processing unit
It can be put by the charging voltage that system controls capacitor in the charging voltage and firing circuit of main discharge capacitor to control single pulse
Electric flux and ignition energy.
Main discharge typical waveform when Fig. 2 is the novel pulse plasma thruster work based on capillary discharging.Its
Middle waveform 1 is main discharge current waveform, and waveform 2 is main discharge voltage waveform.After firing command issues, in spark plug semiconductor table
Face occurs edge flashing and generates the arc discharge that initial charged particles cause thruster yin-yang interpolar.Plasma in electric arc at this time
Volume density is smaller, and conductivity is lower, as bust occurs for the bust principal voltage of arc road resistance.As shown in Fig. 2, principal voltage falls width
Value is Ub, arcing time t1.As arc erosion propellant working medium makes plasma be full of entire capillary cavity and sprays outward
It penetrates, plasma conductivity is in higher horizontal and holding is stablized, and main discharge switchs to the RLC electric discharge of sinusoidal decay oscillation at this time
Until main capacitance energy discharges completely, the duration of RLC electric discharge is t2。
The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations；Although referring to above-described embodiment
Invention is explained in detail, those skilled in the art should understand that；It still can be to above-mentioned each implementation
Technical solution documented by example is modified, or carries out equivalent substitute to part of technical characteristic；And these modification or
It replaces, scope described in various embodiments of the present invention technology that it does not separate the essence of the corresponding technical solution.
Claims (10)
1. a kind of pulsed plasma thruster based on capillary discharging, which is characterized in that the thruster includes: at power supply
Manage unit, semiconductor spark plug, firing circuit, main discharge circuit and propellant working medium；
Voltage needed for the power supply processing unit is used to be supplied to thruster work carries out the main capacitance in main discharge circuit
It charges and powers to firing circuit；
The firing circuit makes semiconductor spark plug that creeping discharge generation initial charged particles occur for exporting high voltage pulse；
The initial charged particles that the semiconductor spark plug generates enter in propellant working medium, are generated by continuous ionization by collision
Plasma；
The propellant working medium is capillary type, and with the generation of plasma, edge flashing shape occurs for propellant working medium surface
At the electric discharge of main capacitance in main discharge circuit；
The main discharge circuit for the electric energy that power supply processing unit provides is stored and is transmitted, ablation propellant working medium simultaneously
Accelerate plasma, main capacitance energy is converted into plasma kinetic energy, to form plasma jet, generates thrust.
2. thruster according to claim 1, which is characterized in that the thruster further include: cathode nozzle, anode and have
Machine glass shell；
The cathode nozzle is for accelerating plasma；
The organic glass shell is for connecting cathode nozzle, anode and propellant working medium.
3. thruster according to claim 2, which is characterized in that the firing circuit includes: ignition capacitor, isolation use
Kenetron, ignition switch and pre-trigger circuit；
The ignition capacitor high-voltage end is connect by isolation kenetron with ignition switch one end, low-pressure end and thruster
Cathode nozzle is connected；
The pre-trigger circuit output pulse signal drive ignition switch generates ignition capacitor to semiconductor spark plug electric discharge
Initial charged particles.
4. thruster according to claim 3, it is characterised in that: the propellant working medium uses solid polytetrafluor ethylene material
Material；
The propellant working medium is coaxial capillary type, being capable of the change of the output parameter according to required for the space tasks of thruster
The length and internal diameter of working medium；
The capillary inner diameter is 1mm~10mm, and length is 9mm~20mm.
5. thruster according to claim 3, it is characterised in that: the pre-trigger circuit includes capacitor group, semiconductor
Switch, control circuit and pulse transformer；
Primary side of the capacitor group for pulse transformer is discharged, and exports high voltage pulse on pulse transformer pair side, is applied
It is added in the filp-flop stage and low-pressure end of ignition switch and switches it on；
The control circuit is for being connected semiconductor switch.
6. thruster according to claim 1, which is characterized in that the material of the semiconductor spark plug semiconductor is to be carbonized
Silicon is substrate, by zirconium dioxide, aluminum oxide, glass and silicon carbide with 17: 22: 12: 49 percent mass ratio sintering and
At, the porosity 5%, water absorption rate 0.8%.
7. thruster according to claim 2, it is characterised in that: the cathode nozzle is divergent nozzle shape, cathode spray
Mouth half angle angle is 15 °~30 °, and length is 10mm~25mm；
Screw assembly is used between the cathode nozzle and organic glass shell and is fitted close.
8. thruster according to claim 2, it is characterised in that: the anode be hollow cylinder shape, the anode with have
Screw assembly is used between machine glass shell, and there are the allowances of 0.8-1.2mm to guarantee the cooperation between propellant working medium.
9. thruster according to claim 1, it is characterised in that: the thruster is worked with impulse form, work when institute
The energy acceptor capacitance and charging voltage of consumption control, and working frequency is 0~1Hz, and pulse working time is 4~5 μ s.
10. thruster according to claim 1, it is characterised in that: the main capacitance capacity is the 1 μ F of μ F~4.5, charging electricity
Pressure is 1kV~3kV, and primary power is 0.5J~20.25J.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710351905.7A CN107091210B (en) | 2017-05-18 | 2017-05-18 | A kind of pulsed plasma thruster based on capillary discharging |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710351905.7A CN107091210B (en) | 2017-05-18 | 2017-05-18 | A kind of pulsed plasma thruster based on capillary discharging |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107091210A CN107091210A (en) | 2017-08-25 |
| CN107091210B true CN107091210B (en) | 2018-12-04 |
Family
ID=59637335
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710351905.7A Active CN107091210B (en) | 2017-05-18 | 2017-05-18 | A kind of pulsed plasma thruster based on capillary discharging |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107091210B (en) |
Families Citing this family (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107587989B (en) * | 2017-10-17 | 2019-01-25 | 北京理工大学 | A kind of double state solid pulsed plasma thrusters of high efficiency |
| CN108301997A (en) * | 2018-01-24 | 2018-07-20 | 上海交通大学 | Pulsed plasma thruster based on Z-PINCH no-spark plugs |
| CN108678920B (en) * | 2018-05-17 | 2019-10-18 | 深圳巡天空间技术有限公司 | Firing circuit and solid ablation pulsed electric thruster |
| CN108869220B (en) * | 2018-06-07 | 2019-08-09 | 西安空间无线电技术研究所 | A kind of propulsion device and propulsion method for Spatial kinematics |
| CN109236594B (en) * | 2018-09-14 | 2020-08-25 | 哈尔滨工业大学 | Low-power magnetized electric propulsion hollow cathode thruster |
| CN110131120B (en) * | 2019-06-28 | 2024-01-19 | 中国人民解放军国防科技大学 | Solid ablation type magnetic plasma thruster |
| CN111712030B (en) * | 2020-05-15 | 2021-09-07 | 西安交通大学 | Capillary system for generating repeated-frequency high-heat-load plasma jet |
| CN111878338B (en) * | 2020-08-20 | 2021-08-27 | 西安交通大学 | Pulse plasma thruster |
| CN113158420B (en) * | 2021-03-03 | 2024-04-30 | 北京大学 | Method and system for determining optimal parameters of capillary tube for proton focusing |
| CN113123936B (en) * | 2021-04-17 | 2022-03-04 | 中国人民解放军国防科技大学 | Grid accelerating micro-cathode arc propulsion system |
| CN113357112A (en) * | 2021-07-02 | 2021-09-07 | 兰州空间技术物理研究所 | Propellant supply module and thruster arcing method |
| CN114001003A (en) * | 2021-10-26 | 2022-02-01 | 北京理工大学 | Double-section coaxial toothed cathode pulse plasma thruster |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4821508A (en) * | 1985-06-10 | 1989-04-18 | Gt-Devices | Pulsed electrothermal thruster |
| US4821509A (en) * | 1985-06-10 | 1989-04-18 | Gt-Devices | Pulsed electrothermal thruster |
| CN1358058A (en) * | 2001-10-25 | 2002-07-10 | 华中科技大学 | Capillary plasma generator |
| CN102678501A (en) * | 2012-05-24 | 2012-09-19 | 中国科学院力学研究所 | Gallium ion field emission micro-thruster |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7302792B2 (en) * | 2003-10-16 | 2007-12-04 | The Johns Hopkins University | Pulsed plasma thruster and method of making |
-
2017
- 2017-05-18 CN CN201710351905.7A patent/CN107091210B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4821508A (en) * | 1985-06-10 | 1989-04-18 | Gt-Devices | Pulsed electrothermal thruster |
| US4821509A (en) * | 1985-06-10 | 1989-04-18 | Gt-Devices | Pulsed electrothermal thruster |
| CN1358058A (en) * | 2001-10-25 | 2002-07-10 | 华中科技大学 | Capillary plasma generator |
| CN102678501A (en) * | 2012-05-24 | 2012-09-19 | 中国科学院力学研究所 | Gallium ion field emission micro-thruster |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107091210A (en) | 2017-08-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107091210B (en) | A kind of pulsed plasma thruster based on capillary discharging | |
| CN106640568B (en) | A kind of dipolar solid ablative-type protective coating plasma accelerator | |
| CN101463763B (en) | Magnetically stabilized plasma flow ignition generator | |
| CN107061210B (en) | A kind of pulsed plasma thruster accelerated based on electrothermal and electromagnetic mixing | |
| CN106523313B (en) | A kind of micropulse plasma thruster | |
| CN210106081U (en) | Solid ablation type magnetic plasma thruster | |
| CN106704133A (en) | Non-trigger type vacuum arc micro thruster using gas storage electrodes | |
| MX2014009643A (en) | Extended cascade plasma gun. | |
| CN107654347B (en) | A kind of high-performance solid ablative-type protective coating pulsed plasma electric propulsion device | |
| CN109737023A (en) | A kind of self breakdown type pulsed plasma thruster of annular vertebral body structure anode | |
| US7408303B2 (en) | Pulsed plasma accelerator and method | |
| CN206592256U (en) | A kind of triggerless micro-vacuum arc propeller of use gas storage electrode | |
| CN109578233B (en) | Ablation type pulse plasma propeller based on multi-anode electrode structure | |
| CN102146902A (en) | High-frequency and high-voltage single electrode plasma thruster | |
| US4063130A (en) | Low impedance electron-beam controlled discharge switching system | |
| Yushkov et al. | On a Mechanism of Ion Acceleration in Vacuum Arc-Discharge Plasma. | |
| RU2542354C1 (en) | Eroding pulse plasma accelerator | |
| CN110486244B (en) | Electromagnetic induction type plasma accelerating device | |
| CN111654967B (en) | Double-jet pulse metal ion plasma propeller | |
| CN108301997A (en) | Pulsed plasma thruster based on Z-PINCH no-spark plugs | |
| CN109673097A (en) | A kind of air-cooled combination electrode plasma generator | |
| RU2664892C1 (en) | Ablative pulse plasma engine | |
| CN118188374A (en) | Plasma jet ignition device and method using energy-containing doping modified working medium | |
| CN219795471U (en) | Satellite electric pushing device and system | |
| CN216017230U (en) | Thermal plasma spray gun |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |