CN107143475B - Multi-stage discharge circuit for laser-supported magnetic plasma thruster - Google Patents
Multi-stage discharge circuit for laser-supported magnetic plasma thruster Download PDFInfo
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- CN107143475B CN107143475B CN201710574468.5A CN201710574468A CN107143475B CN 107143475 B CN107143475 B CN 107143475B CN 201710574468 A CN201710574468 A CN 201710574468A CN 107143475 B CN107143475 B CN 107143475B
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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
Abstract
The invention provides a multistage discharge circuit for a laser-supported magnetic plasma thruster, which adopts a multistage discharge mode to provide discharge energy for the thruster, realizes the respective control of laser ignition, ionization breakdown and discharge acceleration in the working process of the thruster, can distribute energy according to actual requirements, enhances the control capability of the thruster, and effectively improves the energy efficiency of the thruster.
Description
Technical Field
The invention belongs to the field of electric propulsion, relates to a magnetic plasma thruster, and in particular relates to a multistage discharge circuit of the magnetic plasma thruster for laser support.
Background
The magnetic plasma thruster is an electromagnetic acceleration type electric propulsion system, and has remarkable advantages in the aspects of large spacecraft orbit lifting, interplanetary navigation, deep space detection and the like according to the characteristics of high specific impulse, high efficiency, large thrust and the like. According to different working modes, the device can be divided into a steady-state magnetic plasma thruster and a quasi-steady-state magnetic plasma thruster, wherein the quasi-steady-state magnetic plasma thruster has the characteristics of higher efficiency and longer service life. The discharge circuit in the quasi-steady state magnetic plasma thruster has the function of providing quasi-steady state discharge energy.
CN201610273464.9 discloses a laser-supported magnetic plasma thruster, which uses laser-ablated solid material as working medium of the thruster. The problems of complex air supply system, slow dynamic response, serious cathode ablation, large current oscillation and the like of the traditional magnetic plasma thruster are solved, and the magnetic plasma thruster supported by laser and having the advantages of fast dynamic response, high working medium utilization rate and high energy conversion efficiency is provided for a spacecraft. The magnetic plasma thruster supported by the laser adopts a solid working medium, and the working process is as follows: when laser ablates solid working medium, the ablation product is ionized by the high-voltage electric field between the two electrodes to generate partial plasma, and the laser forms breakdown discharge between the two electrodes to generate ionization and accelerate the plasma.
The existing discharging circuit is one-stage discharging, wherein only one charging power supply is used for charging a group of capacitors, and when the breakdown voltage (more than 2000V) is reached, the breakdown and the discharging occur simultaneously, so that a strong arc is formed. When the amplifying circuit is used for the thruster, strong electric arcs are generated when the discharging party is broken down, so that a large amount of heat is generated, solid working media are ablated, serious hysteresis ablation is formed, and waste of working media and energy is caused. And the strong arc can ablate electrode materials, reducing the service life of the thruster.
Disclosure of Invention
The invention aims to provide a multistage discharge circuit for a laser-supported magnetic plasma thruster, which solves the technical problem that the working medium has serious lagging ablation in the discharge process when the conventional discharge circuit is used for the magnetic plasma thruster.
The invention provides a multistage discharge circuit of a magnetic plasma thruster for laser support, which comprises an anode, a cathode, an isolation section and working media for receiving laser incidence, wherein the anode and the cathode are respectively arranged on two opposite sides of the isolation section, and the working media are transversely penetrated in the middle of the isolation section; comprises a pulse breakdown circuit connected in series with a cathode and an anode, a quasi-steady-state discharge circuit connected in series with the cathode and the anode, and a protection circuit connected with one end of the protection circuit and the other end of the protection circuit connected with the anode and the ground,
the pulse breakdown circuit comprises a high-voltage charging power supply, a small-capacity capacitor and a line inductor, wherein the small-capacity capacitor and the line inductor are connected in parallel with the high-voltage charging power supply, the high-voltage charging power supply is connected with one end of the line inductor in parallel with the small-capacity capacitor, and the negative electrode is connected with the negative electrode; the other end of the line inductor is connected with the anode;
the quasi-steady-state discharging circuit comprises a high-power charging power supply, a plurality of charging units and diodes, wherein the anodes, the diodes and the charging units are sequentially connected in series; the plurality of charging units are connected in parallel and then connected in parallel with a high-power charging power supply;
the charging unit comprises a rectifying inductor, a rectifying resistor and a high-capacity capacitor which are sequentially connected in series;
the protection circuit comprises a power consumption resistor and a relay, wherein one end of the power consumption resistor is connected with the anode, and the other end of the power consumption resistor is connected with the relay; the other end of the relay is grounded.
Further, the small capacity capacitance is of the order of μf, and the charging voltage is higher than 2000V. .
Further, the capacitance and the rectification inductance in the quasi-steady-state discharge circuit are calculated according to the following formula
Wherein, the capacitance C q Rectifying inductance L q Characteristic discharge time τ q Number of capacitors n, initial voltage of capacitor V ini Plasma resistance R p Discharge current I q Loop inductance L q 。
Further, the pulse breakdown circuit and the quasi-steady-state discharge circuit are connected in parallel through a diode.
Further, the defined current of the relay is greater than the ratio of the anode voltage to the power dissipation resistance.
The invention has the advantages that:
1. the multistage discharge circuit for the laser-supported magnetic plasma thruster separates the ignition, breakdown and discharge processes through the two circuits, and the two circuits are connected in parallel through the diode, so that the high voltage of the pulse breakdown circuit cannot be transmitted to the quasi-steady-state discharge circuit. The laser ignition is performed in a laser mode, and the laser ignition, pulse breakdown and quasi-steady discharge are respectively controlled in the working process of the thruster, so that energy distribution is performed on the three parts according to actual requirements, the control capability of the thruster is enhanced, and the energy efficiency of the thruster is effectively improved.
2. The multistage discharge circuit for the laser-supported magnetic plasma thruster provided by the invention can calculate and obtain the capacitance and the inductance value in the quasi-steady state discharge circuit according to the discharge requirement of the thruster through the formula (5), and is convenient for adjusting the discharge characteristic of the thruster. The electric potential at two ends of the small-capacity capacitor in the pulse breakdown circuit is high, breakdown discharge is easy to form between two polar plates of the thruster, and the success rate of the thruster discharge is increased.
3. The multistage discharge circuit for the laser-supported magnetic plasma thruster provided by the invention has the advantages that the potential at the two ends of the large capacity capacitor in the quasi-steady state discharge circuit is low, and the requirements on the capacitor and a high-power charging power supply are reduced, so that the manufacturing cost of the whole device is reduced. The protection circuit is added, and the electricity safety of the whole device is improved. Simple structure, simple to operate, stability are high, and energy efficiency is high.
The above and other aspects of the present invention will be made apparent by specific reference to the following description of various embodiments presented in accordance with the multi-stage discharge circuit of a magnetic plasma thruster for laser support.
Drawings
FIG. 1 is a schematic diagram of a multi-stage discharge circuit of a magnetic plasma thruster for laser support provided by the present invention;
FIG. 2 is a schematic diagram of the principle of pulse breakdown discharge in the present invention;
FIG. 3 is a graph showing the voltage-current variation of pulse breakdown discharge with time according to the principle of pulse breakdown discharge according to the preferred embodiment of the present invention;
FIG. 4 is a schematic diagram of the quasi-steady state discharge principle in the present invention;
fig. 5 is a graph showing the pulse breakdown discharge voltage-current variation with time under the quasi-steady state discharge principle of the preferred embodiment of the present invention.
Legend description:
1. a magnetic plasma thruster; 11. an anode; 12. a cathode; 13. an isolation section; 14. working medium; 2. a pulse breakdown circuit; 21. a high voltage charging source; 22. a small capacity capacitor; 23. line inductance; 3. a quasi-steady-state discharge circuit; 31. a high-power charging power supply; 32. a high capacity capacitor; 33. a rectifying resistor; 34. a rectifying inductance; 35. a diode; 4. a protection circuit; 41. a power consumption resistor; 42. and a relay.
Detailed Description
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention.
The discharge circuit provided by the invention can only be used for the laser supporting magnetic plasma thruster disclosed in CN 201610273464.9.
Referring to fig. 1, the multi-stage discharge circuit for a laser-supported magnetic plasma thruster provided by the present invention includes: a pulse breakdown circuit 2, a quasi-steady-state discharge circuit 3 and a protection circuit 4.
The magnetic plasma thruster 1 comprises an anode 11, a cathode 12, an isolation section 13 and a working medium 14. Anode 11 and cathode 12 are disposed on opposite sides of separator segment 13, respectively. The working medium 14 is arranged in the middle of the isolation section 13. The laser beam is incident directly against working fluid 14.
The pulse breakdown circuit 2 is connected in series to the cathode 11 and the anode 12. The pulse breakdown circuit 2 includes a high-voltage charging power supply 21, a small-capacity capacitor 22 connected in parallel with the high-voltage charging power supply 21, and a capacitor 23 connected in series with the high-voltage charging power supply 21. The high-voltage charging power supply 21 charges the small-capacity capacitor 22. The positive electrode of the high-voltage charging power supply 21 connected in parallel with the small-capacity capacitor 22 is connected in series with one end of the line inductor 23. The other end of the line inductance 23 is connected to the anode 11. The negative electrode of the high-voltage charging power supply 21 connected in parallel with the small-capacity capacitor 22 is connected to the cathode 12. Thereby forming a high voltage electric field between the anode 11 and the cathode 12 of the thruster 1 by the pulse breakdown circuit 2. When the laser ignites, a breakdown discharge is formed between the anode 11 and the cathode 12, a plasma channel is established, and the quasi-steady-state discharge circuit 3 is induced to operate.
The quasi-steady-state discharging circuit 3 comprises a high-power charging power supply 31, at least one charging unit and a diode 35, wherein the anode 11, the diode 35 and the charging unit are sequentially connected in series; the plurality of charging units are connected in parallel and then connected in parallel with the high-power charging power supply 31.
The charging unit includes a rectifying inductance 34, a rectifying resistor 33 and a large capacity capacitor 32 connected in series in order. The plurality of charging units are connected in parallel. The rectifying inductance 34 of the first charging unit is connected in series with a diode 35. The high-power charging power supply 31 is used to charge the high-capacity capacitor 32. While the cathode 12 is connected to ground. The method comprises the steps of carrying out a first treatment on the surface of the The other end of the high-power charging power supply 31 is connected in series with the cathode 12;
the quasi-steady-state discharge circuit 3 is used for providing discharge energy for the thruster 1, forming large-current discharge between the anode 12 and the cathode 11 of the thruster 1, and providing strong electromagnetic acceleration for working medium. The diode 35 prevents the high potential of the pulse breakdown circuit 2 from flowing to the quasi-steady-state discharge circuit 3, avoiding the high potential from causing the bulk capacitance 32 to charge beyond a defined voltage.
The protection circuit 4 includes a power consumption resistor 41 and a relay 42 connected in order, and one end of the power consumption resistor 41 is connected to the anode 11, and the other end is connected to the ground through the relay 42. The protection circuit 4 is used for guaranteeing the safe discharge of the thruster 1. When the electric discharge of the thruster 1 fails, the high-voltage electric field between the anode 11 and the cathode 12 and the electric energy stored in the capacitor in the circuit need to be released, at this time, the relay 42 in the protection circuit 4 is opened, the anode 11 is connected to the ground through the power consumption resistor 41, and the power consumption resistor 41 can also release the strong electric field between the anode 11 and the cathode 12 and the electric energy stored in the capacitor in the circuit through heat generation. Thereby ensuring the safety of the whole circuit.
The multistage discharge circuit provided by the invention can effectively improve the energy efficiency of the thruster and provide the laser-supported magnetic plasma thruster with the discharge energy required by quasi-steady discharge. The laser ignition mode is adopted, so that a spark plug and a spark plug ignition circuit are omitted, and simultaneously, the laser ignition energy and the ignition position are convenient to control. According to the invention, the discharge process of the thruster is divided into laser ignition, pulse breakdown and quasi-steady discharge to be respectively controlled, and the energy distribution is carried out on the three parts according to actual requirements, so that the control capability of the thruster is enhanced, and the energy efficiency of the thruster is effectively improved.
Preferably, the small capacitance in the pulse breakdown circuit is of the order of μf, and the charging voltage is higher than 2000V. ( The charging voltage is higher than 2000V because breakdown is thus easily formed, which is obtained from experimental experience. The higher the charging voltage, the easier it is to break down, but the higher the charging voltage the higher the requirements on the charging power supply and the capacitance. The small-capacity capacitor is of mu F magnitude, and laboratory experience shows that the small-capacity capacitor has large capacity and can form a strong arc when a pulse breaks down, so that waste is caused; the breakdown arc formed by the small capacitance of the small capacitance is too weak, so that a plasma channel can not be established, and a quasi-steady-state discharge can not be formed. )
Preferably, the quasi-steady state discharge circuit is a combination of a plurality of bulk capacitances, rectifying resistances and rectifying inductances. (according to the discharge requirement of the thruster, different discharge time and discharge energy can be obtained in a quasi-steady state discharge circuit through the cooperation of different large-capacity capacitors, rectification resistors and rectification inductors.)
Preferably, the capacitance and the rectified inductance in the quasi-steady state discharge circuit are calculated according to the thruster discharge requirement by equation (5). (according to the discharge requirement of the thruster, the capacitance and the rectification inductance value in the quasi-steady-state discharge circuit are obtained through calculation of a formula (5)
Preferably, the pulse breakdown circuit 2 is connected in parallel with the quasi-steady-state discharge circuit 3 via a diode 35. The parallel connection enables both the energy in the pulse breakdown circuit 2 and in the quasi-steady state discharge circuit 3 to be released between the thruster plates and the diode 35 prevents the high voltage of the pulse breakdown circuit 2 from being transmitted towards the quasi-steady state discharge circuit 3.
Preferably, the relay 42 in the protection circuit 4 defines a current greater than the ratio of the voltage of the anode 11 to the power consumption resistor 41.
The multistage discharge circuit for the laser-supported magnetic plasma thruster provided by the invention divides the discharge process into three stages: laser ignition, pulse breakdown, and quasi-steady state discharge. The capacitance capacity in the pulse breakdown circuit is small, and the charging voltage is high, so that breakdown discharge is easy to form between two electrodes of the thruster, and a plasma channel is established between the two electrodes. The plasma channel between the two electrodes is communicated with the two electrodes, so that the quasi-steady state discharge circuit releases energy between the two electrode plates.
Meanwhile, compared with a quasi-steady-state discharge circuit, the pulse breakdown circuit has very small energy, and the electric arc formed between the two polar plates has low energy and can not cause serious ablation on polar plate materials and working media. The quasi-steady-state discharge circuit releases large energy, and most of the energy is completely released between the two plates after the plasma channel is established between the two plates. The multistage discharge circuit can effectively improve the energy efficiency of the thruster.
The principles of the present invention are described below with reference to specific examples.
Principle of pulse breakdown discharge
As shown in fig. 2, the pulse breakdown circuit 2 includes a high-voltage charging power supply 21, a small-capacity capacitor 22, and a line inductance 23. The typical RLC underdamped discharge when pulse breakdown discharge occurs in the thruster 1 has the loop equation of
Wherein C is p 、L p And R is p The capacitance, line inductance and plasma resistance of the pulse breakdown discharge loop, respectively. q is the amount of plate charge.
The pulse breakdown discharge process is satisfied
The condition is an under damped ringing process and the discharge current +.>
Thus, the breakdown discharge current expression can be obtained from equation (1)
V in 0 For the initial voltage of the anode of the thruster,
let it be assumed that the thruster anode initial voltage V 0 =2000V, capacitance C p Line inductance l=3μf p =0.05μh, plasma resistance R p =0.1Ω. The pulse breakdown discharge voltage, current change with time is calculated from equation (2) as shown in fig. 3, which illustrates typical under-damped ringing. The single discharge energy of the pulse breakdown circuit is 6J. It is clear from this that the discharge energy of the pulse breakdown circuit is small compared to the quasi-steady state discharge energy, and the ablation of the solid working medium and the electrode material is very weak. Thereby realizing the protection of working media.
Quasi-steady state discharge principle
As shown in fig. 4, kirchhoff's law for each node of the quasi-steady state discharge circuit is as follows:
v in i For each node voltage in the circuit, I i For each loop current, R p Is the plasma resistance, R q And L q Respectively rectifying resistance and rectifying inductance, C q For capacitance, q i The charge amount is the amount of each loop capacitor, and n is the amount of the capacitor.
Characteristic discharge time tau of quasi-steady-state discharge circuit q And discharge current I q Can be calculated by
Further, capacitance C is obtained q And rectifying inductance L q Is a calculated expression of (2)
Let the initial voltage of the capacitor be V ini Plasma resistance r=100V p =0.01Ω, loop resistance R q =0.01Ω, number of capacitors n=10, tTime of discharge q Discharge current i=1.36 ms q =5000A, the loop inductance L is obtained by calculation of (5) q =0.68 μh, capacitance C q =6.8 mF. The change of the quasi-steady-state discharge voltage and current with time is calculated by the formula (3) as shown in fig. 5, so that the quasi-steady-state discharge circuit can provide a quasi-steady-state discharge waveform. The single discharge energy of the quasi-steady discharge circuit is 340J.
The working process comprises the following steps:
when the thruster 1 works, a high-power charging power supply 31 of a quasi-steady-state discharging circuit 3 is firstly turned on to charge a plurality of parallel high-capacity capacitors 32; at the same time, the high voltage charging power supply 21 of the pulse breakdown circuit 2 is turned on to charge the small capacity capacitor 22 (more than 2000V). The large capacity capacitors 32 in the quasi-steady-state discharging circuit 3 and the small capacity capacitors 22 in the pulse breakdown circuit 2 are connected in parallel to the two electrodes of the thruster 1, the two ends of the small capacity capacitors 22 are high voltage, and the two ends of the large capacity capacitors 32 are low voltage. Since diode 35 in quasi-steady state discharge circuit 3 prevents the conduction of the potential across small capacity capacitor 22 to large capacity capacitor 32, the potential difference across thruster 1 coincides with small capacity capacitor 22 (greater than 2000V). After the laser beam acts on the working medium 14 of the thruster 1, the gas working medium and part of plasma are generated by ablation, so that breakdown discharge is induced between the anode 11 and the cathode 12 of the thruster 1, an electric arc is formed, a plasma channel between two polar plates is established, and the plasma channel is communicated with the quasi-steady-state discharge circuit 3. The electric energy stored by the large-capacity capacitors 32 in the quasi-steady-state discharging circuit 3 is released between the two polar plates of the thruster 1 after being integrated by the rectification resistors 33 and the rectification inductors 34, and a quasi-continuous large-current discharge is formed between the two polar plates of the thruster 1, so that a strong magnetic field is formed, and plasma between the two polar plates is accelerated to be ejected, so that thrust is formed.
When the thruster 1 fails in discharge, a large amount of electric energy is still stored in the circuit, and a high potential difference exists between the small-capacity capacitor 22 and the bipolar plates, which is dangerous. At this time, the high-voltage charging power supply 21 and the high-power charging power supply 31 are turned off first, then the relay 42 in the protection circuit 4 is turned on, the positive electrode of the small-capacity capacitor 22 in the pulse breakdown circuit 2, the positive electrode of the large-capacity capacitor 32 in the quasi-steady-state discharging circuit 3 and the anode 11 of the thruster 1 are connected with the ground through the power consumption resistor 41, and the electric energy stored in the circuit is consumed through the heating of the power consumption resistor. The power consumption resistor is arranged in the protection circuit, even if the power consumption resistor heats, the power consumption resistor can not burn out working media and electrode materials, the power consumption resistor heats usually when the thruster discharges to generate faults, and the electric energy stored in the circuit is released through heating at the moment, so that the danger that the whole circuit stores excessive electric energy due to faults is avoided.
It will be clear to a person skilled in the art that the scope of the present invention is not limited to the examples discussed in the foregoing, but that several variations and modifications are possible without deviating from the scope of the invention as defined in the attached claims. While the invention has been illustrated and described in detail in the drawings and the specification, such illustration and description are to be considered illustrative or exemplary only and not restrictive. The invention is not limited to the disclosed embodiments.
Variations to the disclosed embodiments can be understood and effected by those skilled in the art in practicing the claimed invention, from a study of the drawings, the disclosure, and the appended claims. In the claims, the term "comprising" does not exclude other steps or elements, and the indefinite article "a" or "an" does not exclude a plurality. The mere fact that certain measures are recited in mutually different dependent claims does not indicate that a combination of these measures cannot be used to advantage. Any reference signs in the claims shall not be construed as limiting the scope of the invention.
Claims (4)
1. The multistage discharge circuit comprises an anode, a cathode, an isolation section and a working medium for receiving laser incidence, wherein the anode and the cathode are respectively arranged on two opposite sides of the isolation section, and the working medium is transversely penetrated in the middle of the isolation section;
it is characterized in that the method comprises the steps of,
comprises a pulse breakdown circuit connected in series with the cathode and the anode, a quasi-steady-state discharge circuit connected in series with the cathode and the anode, and a protection circuit connected with one end of the protection circuit and the other end of the protection circuit connected with the anode and the ground,
the pulse breakdown circuit comprises a high-voltage charging power supply, a small-capacity capacitor and a line inductor, wherein the small-capacity capacitor and the line inductor are connected in parallel with the high-voltage charging power supply, the high-voltage charging power supply is connected with one end of the line inductor in parallel with the small-capacity capacitor, and the negative electrode is connected with the negative electrode; the other end of the line inductor is connected with the anode;
the quasi-steady-state discharging circuit comprises a high-power charging power supply, a plurality of charging units and a diode, wherein the anode, the diode and the charging units are sequentially connected in series; the plurality of charging units are connected in parallel and then connected in parallel with the high-power charging power supply;
the charging unit comprises a rectifying inductor, a rectifying resistor and a large-capacity capacitor which are sequentially connected in series;
the protection circuit comprises a power consumption resistor and a relay, wherein one end of the power consumption resistor is connected with the anode, and the other end of the power consumption resistor is connected with the relay; the other end of the relay is grounded;
the capacitance and the rectification inductance in the quasi-steady-state discharge circuit are calculated according to the following formula:
wherein, the capacitance C q Rectifying inductance L q Characteristic discharge time τ q Number of capacitors n, initial voltage of capacitor V ini Plasma resistance R p Discharge current I q Loop inductance L q 。
2. The multistage discharge circuit for a laser-supported magnetic plasma thruster of claim 1, wherein the small capacity capacitance is of the order of μf, and the charging voltage is higher than 2000V.
3. The multi-stage discharge circuit for a laser-supported magnetic plasma thruster of claim 1, wherein the pulse breakdown circuit is connected in parallel with the quasi-steady state discharge circuit by a diode.
4. The multi-stage discharge circuit for a laser-supported magnetic plasma thruster of claim 1, wherein the defined current of the relay is greater than the ratio of the anode voltage to the power consumption resistance.
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| CN110671287B (en) * | 2019-09-25 | 2020-07-31 | 中国人民解放军国防科技大学 | Induction type plasma accelerating device and method |
| CN110671288B (en) * | 2019-09-25 | 2020-07-31 | 中国人民解放军国防科技大学 | Tower section of thick bamboo induction type plasma accelerating device |
| CN110486244B (en) * | 2019-09-25 | 2020-06-30 | 中国人民解放军国防科技大学 | Electromagnetic induction type plasma accelerating device |
| 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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