CN107143475A - The multistage discharge circuit for the magnetic plasma propeller supported for laser - Google Patents
The multistage discharge circuit for the magnetic plasma propeller supported for laser Download PDFInfo
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- CN107143475A CN107143475A CN201710574468.5A CN201710574468A CN107143475A CN 107143475 A CN107143475 A CN 107143475A CN 201710574468 A CN201710574468 A CN 201710574468A CN 107143475 A CN107143475 A CN 107143475A
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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
- F03H1/0081—Electromagnetic plasma thrusters
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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
- F03H1/0006—Details applicable to different types of 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
- Y02E30/00—Energy generation of nuclear origin
- Y02E30/10—Nuclear fusion reactors
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- Combustion & Propulsion (AREA)
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Abstract
The invention provides a kind of multistage discharge circuit for the magnetic plasma propeller supported for laser, multistage discharge mode is used to provide discharge energy for thruster, realize the control respectively to laser ignition, ionization puncture and electric discharge acceleration in the thruster course of work, energy distribution can be carried out to three parts according to actual demand, the control ability of thruster is enhanced, the energy efficiency of thruster is effectively increased.
Description
Technical field
The invention belongs to electric propulsion field, it is related to magnetic plasma propeller, and in particular to a kind of to be used for what laser was supported
The multistage discharge circuit of magnetic plasma propeller.
Background technology
Magnetic plasma propeller is a kind of electromagnetism accelerating type electric propulsion system, with it than leaping high, efficiency high, thrust it is big etc.
Feature has significant advantage in terms of Large Spacecraft lifting track, interplanetary navigation and survey of deep space.According to mode of operation
Difference, can be divided into stable state magnetic plasma propeller and quasi-steady state magnetic plasma propeller, wherein quasi-steady state magnetopasma
Thruster has the characteristics of more efficient, the life-span is longer.Discharge circuit in quasi-steady state magnetic plasma propeller, with offer
The effect of quasi-steady state discharge energy.
The magnetic plasma propeller that a kind of laser is supported is disclosed in CN201610273464.9, this device uses laser
Ablation solid material as thruster working medium.Solve traditional magnetic plasma propeller air supply system complexity, dynamic response
Slowly the problems such as, cathode burning corrosion is serious and high current vibrates, for spacecraft provide a kind of fast dynamic response, working medium utilization rate height,
The magnetic plasma propeller that the high laser of energy conversion efficiency is supported.The magnetic plasma propeller that the laser is supported is using solid
Body working medium, its course of work is：Apply high voltage electric field between the electrode of thruster two, when laser ablation solid working medium, ablation production
Thing is graded gas ions by high voltage electric field ionization generating unit between two electrodes, laser is formed between two electrodes disruptive discharge produce ionization with
Accelerate plasma.
Existing discharge circuit discharges for one-level, only one of which charge power supply, is one group of electric capacity charging, reaching to hit
Puncture and discharge simultaneously when wearing voltage (being more than 2000V) and occur, form hard arc.When the amplifying circuit is used for into the thruster,
Hard arc is produced in disruptive discharge Fang Shihui, so as to produce amount of heat, ablation solid working medium forms serious delayed ablation,
Cause the waste of working medium and energy.And hard arc can ablation electrode material, the service life of reduction thruster.
The content of the invention
It is an object of the invention to provide a kind of multistage discharge circuit for the magnetic plasma propeller supported for laser,
When the invention solves existing discharge circuit for the magnetic plasma propeller, in discharge process there is seriously stagnant in working medium
The technical problem of ablation afterwards.
The present invention provides a kind of multistage discharge circuit for the magnetic plasma propeller supported for laser, magnetopasma
Thruster includes anode, negative electrode, distance piece and the working medium for receiving laser light incident, and the two opposite sides of distance piece set sun respectively
Pole and negative electrode, working medium lateral penetration are arranged in the middle of distance piece；Including pulse breakdown circuit, the string being series on negative electrode and anode
The quasi-steady state discharge circuit and the protection circuit for the other end ground connection that is connected with one end with anode being coupled on negative electrode and anode,
Pulse breakdown circuit includes high voltage charging power supply, the low capacity electric capacity in parallel with high voltage charging power supply and line electricity
Sense, positive pole is connected with one end of line inductance after high voltage charging power supply is in parallel with low capacity electric capacity, and negative pole is connected with negative electrode；
The other end of line inductance is connected with anode；
Quasi-steady state discharge circuit includes high-power charge power supply, multiple charhing units and diode, anode, diode, fills
Electric unit is sequentially connected；It is in parallel with high-power charge power supply after multiple charhing units are in parallel；
Charhing unit includes inductor rectifier, dead resistance and the large bulk capacitance sequentially connected；
Protection circuit includes power consumption resistance and relay, and power consumption resistance one end is connected with anode, the other end and relay
It is connected；The other end ground connection of relay.
Further, low capacity electric capacity is μ F magnitudes, and charging voltage is higher than 2000V..
Further, the capacitance and rectified current inductance value in quasi-steady state discharge circuit are calculated as follows and obtained
Wherein, capacitance Cq, inductor rectifier Lq, characteristic discharge time τq, electric capacity quantity n, electric capacity initial voltage Vini, wait from
Daughter resistance Rp, discharge current Iq, loop inductance Lq。
Further, pulse breakdown circuit is connected with quasi-steady state discharge circuit by diodes in parallel.
Further, the current limit of relay is more than the ratio of anode voltage and power consumption resistance.
The advantage of the invention is that：
1. the multistage discharge circuit for the magnetic plasma propeller supported provided by the present invention for laser, passes through two electricity
Road will light a fire, puncture, discharge process is separated, and two circuits make the high pressure of wherein pulse breakdown circuit not by diodes in parallel
It can be transmitted to quasi-steady state discharge circuit.Lighted a fire with laser mode, by laser ignition, pulse breakdown in the thruster course of work
The control respectively discharged with quasi-steady state, so as to carry out energy distribution to three parts according to actual demand, enhances the control of thruster
Ability processed, effectively increases the energy efficiency of thruster.
2. the multistage discharge circuit for the magnetic plasma propeller supported provided by the present invention for laser, can be according to thrust
Device electric discharge demand passes through formula (5) and calculates the capacitance and inductance value obtained in quasi-steady state discharge circuit, convenient regulation thruster
Flash-over characteristic.Low capacity electric capacity two ends potential in pulse breakdown circuit is high, is easily formed and punctured between thruster two-plate
Electric discharge, adds the success rate of thruster electric discharge.
3. the multistage discharge circuit for the magnetic plasma propeller supported provided by the present invention for laser, therein accurate steady
Large bulk capacitance two ends potential in state discharge circuit is low, reduces the requirement for capacitor and high-power charge power supply, from
And reduce the manufacturing cost of whole device.Protection circuit is added, the electrical safety of whole device is improved.Structure letter
Single, easy for installation, stability is high, and energy efficiency is high.
Specific refer to carries according to the multistage discharge circuit for being used for the magnetic plasma propeller that laser is supported of the present invention
The various embodiments gone out it is described below, will cause apparent in terms of the above and other of the present invention.
Brief description of the drawings
Fig. 1 is the multistage discharge circuit schematic diagram for the magnetic plasma propeller supported provided by the present invention for laser；
Fig. 2 is pulse breakdown discharge principle schematic diagram in the present invention；
Fig. 3 is pulse breakdown discharge voltage-electric current anaplasia at any time under preferred embodiment of the present invention pulse breakdown discharge principle
Change curve synoptic diagram；
Fig. 4 is quasi-steady state discharge principle schematic diagram in the present invention；
Fig. 5 is pulse breakdown discharge voltage-electric current under preferred embodiment of the present invention quasi-steady state discharge principle anaplasia at any time
Change curve synoptic diagram.
Marginal data：
1st, magnetic plasma propeller；11st, anode；12nd, negative electrode；13rd, distance piece；14th, working medium；2nd, pulse breakdown circuit；
21st, high voltage charging power supply；22nd, low capacity electric capacity；23rd, line inductance；3rd, quasi-steady state discharge circuit；31st, high-power charge power supply；
32nd, large bulk capacitance；33rd, dead resistance；34th, inductor rectifier；35th, diode；4th, protection circuit；41st, power consumption resistance；42nd, after
Electrical equipment.
Embodiment
The accompanying drawing for constituting the part of the application is used for providing a further understanding of the present invention, schematic reality of the invention
Apply example and its illustrate to be used to explain the present invention, do not constitute inappropriate limitation of the present invention.
The discharge circuit that the present invention is provided, is simply possible to use in the laser disclosed in CN201610273464.9 and supports magnetic plasma
Thrust body device.
Referring to Fig. 1, the multistage discharge circuit for the magnetic plasma propeller supported provided by the present invention for laser, bag
Include：Pulse breakdown circuit 2, quasi-steady state discharge circuit 3 and protection circuit 4.
Magnetic plasma propeller 1 used includes anode 11, negative electrode 12, distance piece 13 and working medium 14.Anode 11 and negative electrode
12 are respectively arranged at the two opposite sides of distance piece 13.Working medium 14 is arranged at the centre of distance piece 13.Laser beam just enters to working medium 14
Penetrate.
Pulse breakdown circuit 2 is series on negative electrode 11 and anode 12.Pulse breakdown circuit 2 include high voltage charging power supply 21,
23 connected with the low capacity electric capacity 22 of the parallel connection of high voltage charging power supply 21 and with high voltage charging power supply 21.High voltage charging power supply 21 is
Low capacity electric capacity 22 charges.Go here and there one end of positive pole and line inductance 23 after high voltage charging power supply 21 is in parallel with low capacity electric capacity 22
Connection.The other end of line inductance 23 is connected with anode 11.Negative pole after high voltage charging power supply 21 is in parallel with low capacity electric capacity 22 with
Negative electrode 12 is connected.So as to form high voltage electric field between the anode 11 and negative electrode 12 of thruster 1 by pulse breakdown circuit 2.When
Disruptive discharge is formed during laser ignition between the anode 11 and the cathode 12, plasma channel is set up, and then induce quasi-steady state to put
Circuit 3 works.
Quasi-steady state discharge circuit 3, including high-power charge power supply 31, at least one charhing unit and diode 35, anode
11st, diode 35 and charhing unit are sequentially connected；It is in parallel with high-power charge power supply 31 after parallel connection between multiple charhing units.
Charhing unit includes inductor rectifier 34, dead resistance 33 and the large bulk capacitance 32 sequentially connected.Multiple chargings are single
It is in parallel between member.The inductor rectifier 34 of first charhing unit is connected with diode 35.High-power charge power supply 31 is used for big
Capacity 32 charges.Negative electrode 12 is connected with the earth simultaneously.；The other end of high-power charge power supply 31 is connected with negative electrode 12；
Quasi-steady state discharge circuit 3 be used for for thruster 1 provide discharge energy, thruster 1 anode 12 and negative electrode 11 it
Between form heavy-current discharge, provide strong electromagnetic acceleration for working medium.Diode 35 can prevent the high potential of pulse breakdown circuit 2
Flow to quasi-steady state discharge circuit 3, it is to avoid high potential causes the charging of large bulk capacitance 32 to exceed stop voltage.
Protection circuit 4 includes the power consumption resistance 41 and relay 42 sequentially connected, the one end of power consumption resistance 41 and the phase of anode 11
Even, the other end is connected by relay 42 with the earth.Protection circuit 4 is used to ensure the safe-discharge of thruster 1.When thruster 1 is put
, it is necessary to which the electric energy that electric capacity in the high voltage electric field and circuit between anode 11 and negative electrode 12 is stored discharges when electricity breaks down, this
When, the relay 42 in protection circuit 4 is opened, anode 11 is by power consumption resistance 41 with being greatly connected, and power consumption resistance 41 can be with
The electric energy that electric capacity is stored in the highfield and circuit between anode 11 and negative electrode 12 is discharged by generating heat.So that it is guaranteed that whole electricity
The safety on road.
The multistage discharge circuit that the present invention is provided, can effectively improve the energy efficiency of thruster, be the magnetic that laser is supported
Plasma thruster provides the discharge energy needed for quasi-steady state electric discharge.Using laser ignition mode, spark plug and fire are eliminated
Spark plug ignition circuit, while laser ignition energy and the convenient control of ignition location.The discharge process of thruster is divided into by the present invention
Laser ignition, pulse breakdown and quasi-steady state electric discharge are respectively controlled, and are carried out energy distribution to three parts according to actual demand, are increased
The strong control ability of thruster, effectively increases the energy efficiency of thruster.
Preferably, the low capacity electric capacity in pulse breakdown circuit is μ F magnitudes, and charging voltage is higher than 2000V.(charging voltage
It is to puncture because so easily being formed higher than 2000V, is obtained according to experiment experience.Charging voltage is more high more easily to be punctured, but is filled
The higher requirement to charge power supply and electric capacity of piezoelectric voltage is higher.Low capacity electric capacity is μ F magnitudes, laboratory experience, low capacity electric capacity
Capacity conference forms hard arc in pulse breakdown, causes to waste；The puncture electric arc of the small formation of low capacity capacitance is too weak, can
It can will not set up plasma channel, it is impossible to form quasi-steady state electric discharge.)
Preferably, quasi-steady state discharge circuit is the combination of multiple large bulk capacitances, dead resistance and inductor rectifier.(foundation
, can by the cooperation of different large bulk capacitances, dead resistance and inductor rectifier in thruster electric discharge demand, quasi-steady state discharge circuit
Acquisition different discharge time and discharge energy.)
Preferably, the capacitance and rectified current inductance value in quasi-steady state discharge circuit pass through public affairs according to thruster electric discharge demand
Formula (5), which is calculated, to be obtained.(according to thruster electric discharge demand, pass through formula (5) and calculate the electric capacity appearance obtained in quasi-steady state discharge circuit
Amount and rectified current inductance value)
Preferably, pulse breakdown circuit 2 is connected in parallel with quasi-steady state discharge circuit 3 by diode 35.It is connected in parallel
The energy in pulse breakdown circuit 2 and quasi-steady state discharge circuit 3 can be made all to discharge between thruster two-plate, and diode
35 prevent the high pressure of pulse breakdown circuit 2 to be transmitted to quasi-steady state discharge circuit 3.
Preferably, the current limit of relay 42 in protection circuit 4 is more than the ratio of the voltage of anode 11 and power consumption resistance 41.
The multistage discharge circuit for the magnetic plasma propeller supported provided by the present invention for laser divides discharge process
For three phases：Laser ignition, pulse breakdown and quasi-steady state electric discharge.Capacitance in pulse breakdown circuit is small, charging voltage
Height, so that easily forming disruptive discharge between the electrode of thruster two, sets up plasma channel between electrodes.Two electricity
The plasma channel of interpolar connects two electrodes, so as to realize that energy is released between two-plate by quasi-steady state discharge circuit.
Meanwhile, compared to quasi-steady state discharge circuit, the energy of pulse breakdown circuit is very small, is formed between two-plate
Arc energy is low, will not cause serious ablation to plate material and working medium.Quasi-steady state discharge circuit releases energy greatly, works as two-plate
Between set up after plasma channel, this most of energy is all released between two-plate.Using multistage electric discharge electricity of the invention
Road, can effectively improve the energy efficiency of thruster.
The principle of the present invention is illustrated below in conjunction with instantiation.
Pulse breakdown discharge principle
As shown in Fig. 2 pulse breakdown circuit 2 includes high voltage charging power supply 21, low capacity electric capacity 22 and line inductance 23.Push away
Discharged during the 1 pulsing disruptive discharge of power device for typical RLC underdampings, its loop equation is
In formula, Cp、LpAnd RpThe respectively capacitance of pulse breakdown discharge loop, line inductance and plasma resistance.q
For plate charge amount.
Pulse breakdown discharge process is metCondition, is a underdamping convergent oscillation process, and discharge currentTherefore disruptive discharge current expression can be obtained by equation (1)
V in formula0For thruster anode initial voltage,
Assuming that thruster anode initial voltage V0=2000V, capacitance Cp=3 μ F, line inductance Lp=0.05 μ H, wait from
Daughter resistance Rp=0.1 Ω.Then acquisition pulse breakdown discharge voltage, electric current is calculated by formula (2) to change over time such as Fig. 3 institutes
Show, illustrate for typical underdamping convergent oscillation.Pulse breakdown circuit impulse discharge energy is 6J.It follows that compared to standard
Steady-state discharge energy, the discharge energy of pulse breakdown circuit is smaller, and the ablation to solid working medium and electrode material is very weak.So as to
Realize the protection to working medium.
Quasi-steady state discharge principle
As shown in figure 4, can be obtained by each node Kirchhoff's law of quasi-steady state discharge circuit：
V in formulaiFor each node voltage, I in circuitiFor each loop current, RpFor plasma resistance, RqAnd LqIt is respectively each
Dead resistance and inductor rectifier, CqFor capacitance, qiFor the quantity of electric charge of each tank capacitance, n is electric capacity quantity.
Quasi-steady state discharge circuit characteristic discharge time τqWith discharge current IqIt can be calculated by following formula
And then, obtain capacitance CqWith inductor rectifier LqCalculation expression
Assuming that electric capacity initial voltage is Vini=100V, plasma resistance Rp=0.01 Ω, loop resistance Rq=0.01 Ω,
Electric capacity quantity n=10, characteristic discharge time τq=1.36ms, discharge current Iq=5000A, then calculated by formula (5) and obtain loop
Inductance Lq=0.68 μ H, capacitance Cq=6.8mF.Acquisition quasi-steady state discharge voltage, electric current are calculated by formula (3) to change over time
As shown in Figure 5, it can be seen that the quasi-steady state discharge circuit can provide quasi-stationary discharge waveform.Quasi-steady state discharge circuit single is put
Electric flux is 340J.
The course of work：
When thruster 1 works, the high-power charge power supply 31 of quasi-steady state discharge circuit 3 is first turned on, is multiple in parallel
Large bulk capacitance 32 charges；Meanwhile, the high voltage charging power supply 21 of pulse breakdown circuit 2 is opened, is that low capacity electric capacity 22 charges (greatly
In 2000V).The low capacity electric capacity 22 in multiple large bulk capacitances 32 and pulse breakdown circuit 2 in quasi-steady state discharge circuit 3 is simultaneously
Connection is connected to 1 liang of electrode of thruster, and the two ends of low capacity electric capacity 22 are high pressure, and the two ends of large bulk capacitance 32 are low pressure.Due to accurate steady
Diode 35 prevents the two ends potential of low capacity electric capacity 22 to be conducted to large bulk capacitance 32 in state discharge circuit 3, the two poles of the earth of thruster 1
Plate electrical potential difference is consistent with low capacity electric capacity 22 (being more than 2000V).Behind laser beam acting thrust 1 working medium 14 of device, ablation produces gas
Body working medium and part plasma, and then disruptive discharge between the anode 11 of thruster 1 and negative electrode 12 is induced, electric arc is formed, is set up
Plasma channel between two-plate, and then connect quasi-steady state discharge circuit 3.Multiple large bulk capacitances in quasi-steady state discharge circuit 3
The electric energy of 32 storages discharges after being integrated through multiple dead resistances 33 and inductor rectifier 34 between the two-plate of thruster 1,1 liang of thruster
Quasi-continuous heavy-current discharge is formed between pole plate, and then forms high-intensity magnetic field, accelerates the plasma between two-plate to spray, so that
Form thrust.
When the electric discharge of thruster 1 is broken down, a large amount of electric energy, and low capacity electric capacity 22 and two-plate are still stored in circuit
Between there is very high electrical potential difference, it is extremely dangerous.High voltage charging power supply 21 and high-power charge power supply 31 are now first shut off, then
The relay 42 in protection circuit 4 is opened, by the positive pole of low capacity electric capacity 22, the quasi-steady state discharge circuit 3 in pulse breakdown circuit 2
In the positive pole of large bulk capacitance 32, the anode 11 of thruster 1 be connected by power consumption resistance 41 with the earth, the electric energy stored in circuit is logical
Cross the consumption of power consumption resistance heating.Power consumption resistance does not result in working medium and electrode material even if heating in the protection circuit yet
Ablation, power consumption resistance heating generally occurs when thruster electric discharge is broken down, the electric energy for now being stored circuit by generating heat
Release, it is to avoid danger of the whole circuit due to failed storage excessive amount of electrical energy.
Those skilled in the art will be clear that the scope of the present invention is not restricted to example discussed above, it is possible to which it is carried out
Some changes and modification, the scope of the present invention limited without departing from appended claims.Although oneself is through in accompanying drawing and explanation
The present invention is illustrated and described in book in detail, but such explanation and description are only explanations or schematical, and it is nonrestrictive.
The present invention is not limited to the disclosed embodiments.
By to accompanying drawing, the research of specification and claims, when implementing the present invention, those skilled in the art can be with
Understand and realize the deformation of the disclosed embodiments.In detail in the claims, term " comprising " is not excluded for other steps or element,
And indefinite article " one " or " one kind " be not excluded for it is multiple.The some measures quoted in mutually different dependent claims
The fact does not mean that the combination of these measures can not be advantageously used.Any reference marker in claims is not constituted pair
The limitation of the scope of the present invention.
Claims (5)
1. a kind of multistage discharge circuit for the magnetic plasma propeller supported for laser, the magnetic plasma propeller bag
Anode, negative electrode, distance piece and the working medium for receiving the laser light incident are included, the two opposite sides of the distance piece set institute respectively
Anode and the negative electrode are stated, the working medium lateral penetration is arranged in the middle of the distance piece；
Characterized in that,
Including be series on the negative electrode and the anode pulse breakdown circuit, be series on the negative electrode and the anode
Quasi-steady state discharge circuit and the protection circuit for the other end ground connection that is connected with one end with the anode,
The pulse breakdown circuit includes high voltage charging power supply, the low capacity electric capacity in parallel with high voltage charging power supply and line electricity
Sense, positive pole is connected with one end of the line inductance after the high voltage charging power supply is in parallel with the low capacity electric capacity, negative pole
It is connected with the negative electrode；The other end of the line inductance is connected with the anode；
The quasi-steady state discharge circuit includes high-power charge power supply, multiple charhing units and diode, the anode, described two
Pole pipe, the charhing unit are sequentially connected；It is in parallel with the high-power charge power supply after multiple charhing units are in parallel；
The charhing unit includes inductor rectifier, dead resistance and the large bulk capacitance sequentially connected；
The protection circuit includes power consumption resistance and relay, and described power consumption resistance one end is connected with the anode, the other end
It is connected with the relay；The other end ground connection of the relay.
2. it is used for the multistage discharge circuit for the magnetic plasma propeller that laser is supported according to claim 1, it is characterised in that institute
Low capacity electric capacity is stated for μ F magnitudes, charging voltage is higher than 2000V.
3. it is used for the multistage discharge circuit for the magnetic plasma propeller that laser is supported according to claim 1, it is characterised in that institute
State the capacitance in quasi-steady state discharge circuit and rectified current inductance value is calculated as follows and obtained
Wherein, capacitance Cq, inductor rectifier Lq, characteristic discharge time τq, electric capacity quantity n, electric capacity initial voltage Vini, plasma
Resistance Rp, discharge current Iq, loop inductance Lq。
4. it is used for the multistage discharge circuit for the magnetic plasma propeller that laser is supported according to claim 1, it is characterised in that institute
Pulse breakdown circuit is stated to be connected by diodes in parallel with the quasi-steady state discharge circuit.
5. it is used for the multistage discharge circuit for the magnetic plasma propeller that laser is supported according to claim 1, it is characterised in that institute
The current limit for stating relay is more than the ratio of the anode voltage and the power consumption resistance.
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| CN110486244A (en) * | 2019-09-25 | 2019-11-22 | 中国人民解放军国防科技大学 | A kind of electromagnetic induction type plasma accelerator |
| CN110671288A (en) * | 2019-09-25 | 2020-01-10 | 中国人民解放军国防科技大学 | Tower section of thick bamboo induction type plasma accelerating device |
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| CN111577564A (en) * | 2020-06-30 | 2020-08-25 | 中国人民解放军国防科技大学 | Single-stage composite double-pulse enhanced ionization type induction pulse plasma thruster |
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| CN110486244A (en) * | 2019-09-25 | 2019-11-22 | 中国人民解放军国防科技大学 | A kind of electromagnetic induction type plasma accelerator |
| CN110671288A (en) * | 2019-09-25 | 2020-01-10 | 中国人民解放军国防科技大学 | Tower section of thick bamboo induction type plasma accelerating device |
| CN110671287A (en) * | 2019-09-25 | 2020-01-10 | 中国人民解放军国防科技大学 | Induction type plasma accelerating device and method |
| CN111577564A (en) * | 2020-06-30 | 2020-08-25 | 中国人民解放军国防科技大学 | Single-stage composite double-pulse enhanced ionization type induction pulse plasma thruster |
| CN114611324A (en) * | 2022-03-28 | 2022-06-10 | 北京航空航天大学 | Fault diagnosis method for high-power magnetic plasma electric propulsion system |
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