CN110768564B - Composite thruster load self-adaptive power supply system and power supply method - Google Patents
Composite thruster load self-adaptive power supply system and power supply method Download PDFInfo
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- H03—ELECTRONIC CIRCUITRY
- H03K—PULSE TECHNIQUE
- H03K3/00—Circuits for generating electric pulses; Monostable, bistable or multistable circuits
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- H03K3/57—Generators characterised by the type of circuit or by the means used for producing pulses by the use of an energy-accumulating element discharged through the load by a switching device controlled by an external signal and not incorporating positive feedback the switching device being a semiconductor device
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Abstract
The invention relates to a load self-adaptive power supply system and a power supply method for a composite thruster, and belongs to the technical field of power supplies. A composite thruster load self-adaptive power supply system comprises an ionization module, a control module and a plasma acceleration module, and can output high voltage required by the ionization of working medium gas of a thruster and large current required by the acceleration of plasma; the ionization module is coupled and output through a pulse transformer, the low potential end of a secondary coil of the pulse transformer is connected with the cathode of the thruster, and the high potential end of the secondary coil of the pulse transformer is connected with the energy storage capacitor of the plasma acceleration module in series and then connected with the anode of the thruster and grounded; the outputs of the two modules are automatically switched according to the load change, and the reliable isolation between the low-voltage plasma accelerating module and the ionizing module is realized through the secondary coil of the pulse transformer.
Description
Technical Field
The invention relates to a load self-adaptive power supply system and a power supply method for a composite thruster, and belongs to the technical field of power supplies.
Background
The composite thruster is a novel thruster formed by skillfully combining a chemical propulsion method and an electric propulsion method. In a pulse repetition frequency working mode, in a pulse period, a working medium consisting of fuel and oxidant is firstly broken down by high voltage to generate gas discharge and be ignited to induce chemical combustion reaction; the plasma generated by discharge and combustion can be further accelerated to be sprayed under the action of Lorentz force generated by the interaction of large current and self-induced magnetic field thereof.
The working principle of the composite thruster has certain similarity with that of the existing magnetic plasma thruster, and the composite thruster needs high voltage to puncture working medium gas to discharge and needs large current to maintain discharge and accelerate. Therefore, the load change laws of the two thrusters are very similar, and the impedance of the thrusters is greatly changed before and after the gas breakdown. In the gas discharge process, the impedance of the thruster is gradually reduced from the approximate infinity, and after a stable discharge path is established between the cathode and the anode, the impedance is reduced to the magnitude of dozens of milliohms and tends to be stable. The power supply system is connected between the cathode and the anode of the thruster, and the front and back output modes of the power supply are greatly changed due to the fact that the impedance of the thruster jumps before and after gas breakdown. In the gas breakdown process, a power supply system needs to output high voltage for gas breakdown, and the output current of the thruster is very small due to the fact that the impedance of the thruster is large at the moment; after the stable discharge is established, the power supply system needs to output a large current for accelerating the plasma, and because the impedance of the thruster is extremely small at this time, the output voltage is generally about hundred volts.
The power supply system of the existing magnetic plasma thruster generally comprises a high-voltage and low-current generation module and a low-voltage and plasma acceleration module, wherein the two modules are respectively connected between a cathode and an anode of the thruster in a parallel mode, and the outputs of the two modules are respectively controlled by two switches. The power supply structure has the following outstanding problems: (1) the output control of each module is realized by controlling the on and off of the corresponding switch, the on time sequence of the corresponding switches of the two modules is controlled by the delay module, and the delay is determined by manual continuous adjustment according to the actual working condition, so that the self-adaptive switching of the load cannot be realized. (2) The two modules are connected in parallel, and the isolation between the two modules is generally realized by adding a plurality of diodes in a low-voltage and high-current module for protection. Since the diode is easily damaged at a high voltage, reliability is to be improved.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the ionization module is coupled and output through a pulse transformer, the low potential end of a secondary coil of the pulse transformer is connected with the cathode of the thruster, the high potential end of the secondary coil of the pulse transformer is connected with an energy storage capacitor of the plasma acceleration module in series and then connected with the anode of the thruster and grounded, the outputs of the two modules are automatically switched according to load changes, reliable isolation between the low-voltage plasma acceleration module and the load of the thruster is realized through the secondary coil of the pulse transformer, and the circuit structure is simplified.
The purpose of the invention is realized by the following technical scheme:
a composite thruster load self-adaptive power supply system is used for supplying power to a thruster and comprises an ionization module, a plasma acceleration module and a control module;
the ionization module comprises a charging power supply, a pulse capacitor and a pulse transformer; the plasma accelerating module comprises a direct current power supply and an energy storage capacitor; the direct current power supply is used for charging the energy storage capacitor;
the charging power supply is used for charging the pulse capacitor, and the pulse capacitor is used for supplying power to the pulse transformer; the low-potential end of the secondary coil of the pulse transformer is connected with the cathode of the thruster; the high potential end of the secondary coil is connected with the anode of the thruster after being connected with the energy storage capacitor in series;
the control module is used for controlling the charging or discharging of the pulse capacitor and the energy storage capacitor.
The load self-adaptive power supply system of the composite thruster is characterized in that when the pulse capacitor is charged to a rated voltage, the control module controls the charging power supply to stop charging the pulse capacitor.
The load self-adaptive power supply system of the composite thruster is characterized in that the ionization module further comprises a discharge switch, a charging resistor, a discharge resistor, a damping resistor and a damping diode; one end of the charging power supply is connected with the other end of the charging power supply after being sequentially connected with the charging resistor, the discharging resistor and the discharging switch; the pulse capacitor, the damping resistor and the damping diode are connected with the discharge resistor and the discharge switch in parallel; the damping resistor and the damping diode are connected with the primary coil of the pulse transformer in parallel.
The load self-adaptive power supply system of the composite thruster is characterized in that when the pulse capacitor supplies power to the pulse transformer, the control module controls the discharge switch to be closed.
The load self-adaptive power supply system of the composite thruster is characterized in that the discharge switch adopts a hydrogen thyratron.
The load self-adaptive power supply system of the composite thruster is characterized in that the boosting ratio of the pulse transformer is more than or equal to 1: 10.
The load self-adaptive power supply system of the composite thruster is characterized in that the control module controls the closing repetition frequency of the discharge switch to be less than or equal to 100 Hz.
A composite thruster load self-adaptive power supply method adopts the composite thruster load self-adaptive power supply system and comprises the following steps:
s10, the control module controls the charging power supply and the direct current power supply to respectively charge the pulse capacitor and the energy storage capacitor;
s20, when the pulse capacitor is charged to the rated voltage, the control module controls the charging power supply to stop charging the pulse capacitor;
and S30, the control module controls the discharge switch to be conducted, the pulse capacitor and the energy storage capacitor supply power to the thruster at the same time, and the pulse capacitor supplies power to the thruster through the pulse transformer.
In the above composite thruster load adaptive power supply method, after S30, S40 turns off the discharge switch when the discharge current of the pulse capacitor is less than or equal to the turn-on threshold of the discharge switch.
The self-adaptive power supply method for the load of the composite thruster repeats S10-S40, and the self-adaptive power supply system for the load of the composite thruster periodically supplies power to the thruster.
Compared with the prior art, the invention has the following beneficial effects:
(1) the invention provides a load self-adaptive power supply system of a composite thruster, wherein an ionization module is coupled and output through a pulse transformer, the low potential end of a secondary coil of the pulse transformer is connected with the cathode of the thruster, the high potential end of the secondary coil of the pulse transformer is connected with an energy storage capacitor of a plasma acceleration module in series and then connected with the anode of the thruster and connected with the ground in parallel, and the power supply system can output high voltage required by gas ionization and large current required by plasma acceleration;
(2) compared with the existing power supply structure, the load self-adaptive power supply system of the composite thruster has the advantages that the output of the ionization module and the output of the plasma acceleration module can be automatically switched according to the impedance change of the thruster, and the reliable isolation between the plasma acceleration module and the ionization module can be realized through the secondary coil of the transformer.
Drawings
Fig. 1 is a circuit configuration of a power supply system according to embodiment 3 of the present invention;
fig. 2 is a working timing sequence of the power supply system in embodiment 3 of the present invention;
fig. 3 is a simulation circuit model of a power system according to embodiment 4 of the present invention;
fig. 4 is a simulation verification waveform of the power system in embodiment 4 of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, embodiments of the present invention will be described in detail with reference to the accompanying drawings.
Example 1:
a composite thruster load self-adaptive power supply system is used for supplying power to a thruster and comprises an ionization module, a plasma acceleration module and a control module;
the ionization module comprises a charging power supply, a pulse capacitor C1, a pulse transformer T1, a discharge switch S1, a charging resistor R1, a discharge resistor R2, a damping resistor R3 and a damping diode D1, wherein the discharge switch S1 adopts a hydrogen thyristor, and the voltage boosting ratio of the pulse transformer T1 is more than or equal to 1: 10. One end of the charging power supply is connected with the other end of the charging power supply after being sequentially connected with the charging resistor R1, the discharging resistor R2 and the discharging switch S1; the pulse capacitor C1, the damping resistor R3 and the damping diode D1 are connected in parallel with the discharge resistor R2 and the discharge switch S1; the damping resistor R3 and the damping diode D1 are connected in parallel with the primary coil of the pulse transformer T1.
The plasma accelerating module comprises a direct current power supply and an energy storage capacitor C2; the dc power supply is used to charge a storage capacitor C2,
the charging power supply is used for charging a pulse capacitor C1, the pulse capacitor C1 is used for supplying power to a pulse transformer T1, and when the pulse capacitor C1 is charged to a rated voltage, the control module controls the charging power supply to stop charging the pulse capacitor C1; the low potential end of the secondary coil of the pulse transformer T1 is connected with the cathode of the thruster; the high potential end of the secondary coil is connected with the anode of the thruster after being connected with the energy storage capacitor C2 in series;
the control module is used for controlling the charging or discharging of the pulse capacitor C1 and the energy storage capacitor C2. When the pulse capacitor C1 supplies power to the pulse transformer T1, the control module controls the discharge switch S1 to be closed. The control module controls the closing repetition frequency of the discharge switch S1 to be less than or equal to 100 Hz.
Example 2:
a composite thruster load self-adaptive power supply method adopts the composite thruster load self-adaptive power supply system described in embodiment 1, and comprises the following steps:
s10, the control module controls the charging power supply and the direct current power supply to respectively charge the pulse capacitor C1 and the energy storage capacitor C2;
s20, when the pulse capacitor C1 is charged to the rated voltage, the control module controls the charging power supply to stop charging the pulse capacitor C1;
s30, the control module controls the discharge switch S1 to be switched on, the pulse capacitor C1 and the energy storage capacitor C2 supply power to the thruster at the same time, and the pulse capacitor C1 supplies power to the thruster through a pulse transformer T1;
s40, when the discharge current of the pulse capacitor C1 is less than or equal to the conducting threshold of the discharge switch S1, the discharge switch S1 is turned off.
And S50, repeating S10-S40, and periodically supplying power to the thruster by the composite thruster load self-adaptive power supply system.
Example 3:
a composite thruster load self-adaptive power supply system comprises an ionization module, a control module and a plasma acceleration module; the ionization module is coupled and output through a pulse transformer, the low potential end of a secondary coil of the pulse transformer is connected with the cathode of the thruster, and the high potential end of the secondary coil of the pulse transformer is connected with the energy storage capacitor of the plasma acceleration module in series and then connected with the anode of the thruster and grounded; the control module is used for controlling charging and discharging of a pulse capacitor of the ionization module, controlling output and termination of a charging power supply and controlling enabling and termination of a direct current power supply of the plasma acceleration module.
The ionization module consists of a charging power supply, a pulse capacitor C1, a pulse transformer T1, a discharge switch S1, a charging resistor R1, a discharge resistor R2, a damping resistor R3 and a damping diode D1 and is used for generating high-voltage pulses required by gas breakdown and ionization of the thruster.
The plasma accelerating module consists of a direct-current power supply and an energy storage capacitor C2 which are connected in parallel and used for generating large current required by the acceleration of the plasma of the thruster.
The charging power supply is a direct current voltage-stabilizing source, the pulse capacitor C1 is charged at the initial stage of each working period, and when the voltage is charged to the rated voltage, the control module outputs a termination signal to stop the direct current voltage-stabilizing source.
The discharging switch S1 adopts a hydrogen thyratron, the control module controls the discharging switch S1 to be switched on when the pulse capacitor C1 is charged to the rated voltage in each pulse period, and the discharging switch S1 is automatically switched off when the discharging current of the pulse capacitor C1 is smaller than the switching-on threshold of the discharging switch S1.
The direct current power supply is a direct current voltage stabilizing power supply and is always in an enabling state during the working period of the thruster, almost no output current exists when the thruster is in a high impedance state, and large current is output when the impedance of the thruster is lowered.
The invention will be further described with reference to the accompanying drawings.
As shown in fig. 1, the ionization module is composed of a charging power supply, a pulse capacitor C1, a pulse transformer T1, a discharge switch S1, a charging resistor R1, a discharge resistor R2, a damping resistor R3, and a damping diode D1, and the plasma acceleration module is composed of a dc power supply and an energy storage capacitor C2.
The working sequence of the composite thruster load adaptive power supply system is shown in figure 2. The pulse repetition frequency mode is adopted, and the specific working process is as follows:
(1) after the thruster is started, on the premise that the thruster acceleration cavity finishes the filling of the working medium gas, the control module can generate an enabling control signal which comprises a charging power supply enabling signal and a direct-current power supply enabling signal, so that the charging power supply starts to charge the pulse capacitor C1, and the direct-current power supply charges the energy storage capacitor C2.
(2) When the pulse capacitor C1 is charged to the rated voltage, the control module controls the charging power supply to stop outputting; the DC power supply enables the energy storage capacitor C2 to be rapidly charged to a rated voltage;
monitoring the voltage of the pulse capacitor C1 by using but not limited to a voltmeter, and monitoring the voltage of the energy storage capacitor C2 by using but not limited to a voltmeter; the control module judges whether the pulse capacitor is charged to the rated voltage or not and whether the energy storage capacitor C2 is charged to the rated voltage or not according to the monitoring result.
(3) In the power supply system, the discharge switch S1 employs a hydrogen thyristor. After the working medium gas is injected, the control module controls the discharge switch S1 to be switched on, the pulse capacitor C1 starts to discharge, and high-voltage pulses are output to a position between the cathode and the anode of the thruster at the secondary side of the pulse transformer T1, so that the gas starts to be broken down and ionized.
(4) In the initial stage of gas breakdown, the cathode and the anode of the thruster are in a high impedance state, the output current of the direct current power supply is very small, and the working energy of the thruster is mainly provided by the ionization module. Along with the increase of the gas ionization degree, the impedance between the cathode and the anode of the thruster is gradually reduced, the output current of the direct current power supply is gradually increased, the output current of the ionization module is gradually reduced, when the discharge current of the pulse capacitor C1 is lower than the conduction threshold of the discharge switch S1, the S1 is automatically turned off, and the energy source of the thruster is automatically switched to be provided by the direct current power supply. The direct current power supply keeps an enabling state all the time in the working process of the thruster, and when the voltage of the energy storage capacitor C2 is lower than the preset voltage, the direct current power supply is timely supplemented.
(5) And (3) under the action of large current, the plasma generated by discharge is sprayed out from a nozzle at the rear end of the thruster at a high speed under the acceleration of Lorentz force, and after the working medium gas in the acceleration cavity of the thruster is exhausted, the load of the thruster is restored to a high-impedance state, and a pulse working cycle is finished.
The next pulse duty cycle will repeat steps (1) - (5).
(6) The thruster stops working after working for n pulse periods, the control module gives out a direct current power supply stop signal, and an operator cuts off the power of the whole power supply system and the whole gas supply system.
Example 4:
the following describes the simulation verification of the circuit reasonableness of the power supply system by using a matlab/simulink tool. Fig. 3 is a simulation circuit model of the power system, in which the ionization module is composed of a charging power supply, a pulse capacitor C1, a pulse transformer T1, a discharge switch S1, a charging resistor R1, a discharge resistor R2, a damping resistor R3, and a damping diode D1; the plasma accelerating module consists of a direct-current power supply and an energy storage capacitor C2; the equivalent load is composed of resistors R4 and R5 and a switching control switch S2. The simulation parameters are set as follows: the output voltage of the charging power supply is 600V; the output voltage of the direct current power supply is 100V; the resistors R1, R2 and R3 respectively take the values of 100 ohms, 0.0001 ohms and 0.01 ohms; the values of the capacitors C1 and C2 are 0.05 microfarad and 0.5 farad respectively; the boosting ratio of the transformer T1 is 1: 2; the values of R4 and R5 are 0.1 ohm and 10k ohm respectively, the values correspond to the low impedance state and the high impedance state of the load respectively, the load impedance state switching is controlled through an impedance change enabling signal, the switch S2 is disconnected when the enabling signal is in a low level, and the switch S2 is closed when the enabling signal is in a high level and is switched to the low impedance state corresponding to the high impedance state; the repetition frequency of the discharge switch enable signal is 90Hz, and the pulse width is 50 us; the impedance change enable signal is synchronously delayed by 16us from the discharge switch enable signal, and has a pulse width of 200 us.
Fig. 4 is a simulation verification waveform in one pulse duty cycle, which includes four portions of a load current waveform, a load voltage waveform, a discharge switch enable signal waveform, and an impedance change enable signal waveform. When the load is in a high impedance state, corresponding load current and voltage waveforms are as shown in 1(a) and 1(b) in fig. 4, the voltage amplitude of the two ends of the load is 100V, which is equal to the output voltage of the plasma acceleration module, and because the load resistance is very large, the output current of the plasma acceleration module is very small at this time, and the current amplitude of the load end is about 10 mA; when the discharge switch S1 is triggered to turn on, the pulse capacitor C1 starts to discharge, and the ionization module outputs a high-voltage pulse through the secondary coil of the transformer T1, because the switch S2 is in an off state, the load still maintains a high impedance state at this time, the corresponding load current and voltage waveforms are as shown in fig. 4 (a) and 2(b), the amplitude of the high-voltage pulse is about 1200V, and the amplitude of the corresponding current pulse rises to about 120 mA; when the switch S2 is triggered to turn on by 16us compared with the switch S1, the load impedance is switched to a low impedance state, the output current of the plasma acceleration module will increase rapidly, the corresponding load current and voltage waveforms are as shown in fig. 4 (a) and 3(b), it can be seen that the load end is automatically switched to be supplied with power by the plasma acceleration module, the voltage amplitude at the two ends of the load decreases rapidly to 100V, and correspondingly, the load current amplitude increases rapidly to about 1000A; when the load returns to the high impedance state, the load current and voltage waveforms return to the 1(a) and 1(b) states, and one pulse duty cycle ends. The above simulation results verify the scientificity and rationality of the invention.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Claims (5)
1. A composite thruster load self-adaptive power supply system is used for supplying power to a thruster and is characterized by comprising an ionization module, a plasma acceleration module and a control module;
the ionization module comprises a charging power supply, a pulse capacitor (C1) and a pulse transformer (T1); the plasma accelerating module comprises a direct current power supply, an energy storage capacitor (C2); the direct current power supply is used for charging an energy storage capacitor (C2);
the charging power supply is used for charging a pulse capacitor (C1), and the pulse capacitor (C1) is used for supplying power to a pulse transformer (T1); the low potential end of the secondary coil of the pulse transformer (T1) is connected with the cathode of the thruster; the high potential end of the secondary coil is connected with the anode of the thruster after being connected with the energy storage capacitor (C2) in series;
the control module is used for controlling the charging or discharging of the pulse capacitor (C1) and the energy storage capacitor (C2);
the ionization module further comprises a discharge switch (S1), a charging resistor (R1), a discharging resistor (R2), a damping resistor (R3), and a damping diode (D1); one end of the charging power supply is connected with the other end of the charging power supply after being sequentially connected with a charging resistor (R1), a discharging resistor (R2) and a discharging switch (S1) in series; the pulse capacitor (C1), the damping resistor (R3) and the damping diode (D1) are connected in series and then are connected in parallel with a series part consisting of a discharge resistor (R2) and a discharge switch (S1); the damping resistor (R3) is connected in series with the damping diode (D1) and then connected in parallel with the primary coil of the pulse transformer (T1);
when the pulse capacitor (C1) is charged to the rated voltage, the control module controls the charging power supply to stop charging the pulse capacitor (C1);
when the pulse capacitor (C1) supplies power to a pulse transformer (T1), the control module controls a discharge switch (S1) to be closed; the control module controls a discharge switch (S1) to be conducted, and a pulse capacitor (C1) and an energy storage capacitor (C2) supply power to the thruster simultaneously, wherein the pulse capacitor (C1) supplies power to the thruster through a pulse transformer (T1);
the boosting ratio of the pulse transformer (T1) is more than or equal to 1: 10;
the control module controls the closing repetition frequency of the discharge switch (S1) to be less than or equal to 100 Hz.
2. The composite thruster load adaptive power supply system according to claim 1, wherein the discharge switch (S1) adopts a hydrogen thyristor.
3. A composite thruster load adaptive power supply method, characterized in that, the composite thruster load adaptive power supply system of claim 1 or 2 is adopted, comprising the following steps:
s10, the control module controls the charging power supply and the direct current power supply to respectively charge the pulse capacitor (C1) and the energy storage capacitor (C2);
s20, when the pulse capacitor (C1) is charged to the rated voltage, the control module controls the charging power supply to stop charging the pulse capacitor (C1);
and S30, the control module controls a discharge switch (S1) to be conducted, and the pulse capacitor (C1) and the energy storage capacitor (C2) supply power to the thruster simultaneously, wherein the pulse capacitor (C1) supplies power to the thruster through a pulse transformer (T1).
4. The composite thruster load adaptive power supply method according to claim 3, wherein after S30, when a discharge current of the pulse capacitor (C1) is less than or equal to a turn-on threshold of the discharge switch (S1), S40, the discharge switch (S1) is turned off.
5. The self-adaptive power supply method for the load of the composite thruster is characterized in that S10-S40 are repeated, and the self-adaptive power supply system for the load of the composite thruster supplies power to the thruster periodically.
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005295654A (en) * | 2004-03-31 | 2005-10-20 | Kobe Steel Ltd | Pulse power unit |
| CN102577078A (en) * | 2009-10-23 | 2012-07-11 | 株式会社岛津制作所 | Pulse voltage generating circuit, discharge circuit, and emission analyzer using the circuits |
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| CN104935306B (en) * | 2015-06-02 | 2018-06-01 | 沈阳理工大学 | A kind of high power pulse gas switch trigger |
| CN106357147B (en) * | 2016-09-30 | 2019-02-05 | 西安交通大学 | A kind of high-effect high current combination wave generation circuit |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005295654A (en) * | 2004-03-31 | 2005-10-20 | Kobe Steel Ltd | Pulse power unit |
| CN102577078A (en) * | 2009-10-23 | 2012-07-11 | 株式会社岛津制作所 | Pulse voltage generating circuit, discharge circuit, and emission analyzer using the circuits |
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