CN114977462A - MPPT control device, method and equipment applied to satellite electric propulsion system - Google Patents

MPPT control device, method and equipment applied to satellite electric propulsion system Download PDF

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CN114977462A
CN114977462A CN202210755005.XA CN202210755005A CN114977462A CN 114977462 A CN114977462 A CN 114977462A CN 202210755005 A CN202210755005 A CN 202210755005A CN 114977462 A CN114977462 A CN 114977462A
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circuit
resistor
mppt
reference voltage
output
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Inventor
董梦雪
杨亚红
夏晨泰
蓝建宇
许多
余任奇
黄军
刘勇
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Shanghai Institute of Space Power Sources
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Shanghai Institute of Space Power Sources
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    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
    • H02J7/34—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering
    • H02J7/35—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering with light sensitive cells
    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05F—SYSTEMS FOR REGULATING ELECTRIC OR MAGNETIC VARIABLES
    • G05F1/00—Automatic systems in which deviations of an electric quantity from one or more predetermined values are detected at the output of the system and fed back to a device within the system to restore the detected quantity to its predetermined value or values, i.e. retroactive systems
    • G05F1/66—Regulating electric power
    • G05F1/67—Regulating electric power to the maximum power available from a generator, e.g. from solar cell
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
    • H02J7/0047—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with monitoring or indicating devices or circuits
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
    • H02J7/0068—Battery or charger load switching, e.g. concurrent charging and load supply
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
    • H02J7/007—Regulation of charging or discharging current or voltage
    • H02J7/00712—Regulation of charging or discharging current or voltage the cycle being controlled or terminated in response to electric parameters
    • 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
    • Y02E10/00—Energy generation through renewable energy sources
    • Y02E10/50—Photovoltaic [PV] energy
    • Y02E10/56—Power conversion systems, e.g. maximum power point trackers

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  • Engineering & Computer Science (AREA)
  • Power Engineering (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Sustainable Energy (AREA)
  • Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • General Physics & Mathematics (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Automation & Control Theory (AREA)
  • Control Of Electrical Variables (AREA)

Abstract

The invention discloses an MPPT control device, a method and equipment applied to a satellite electric propulsion system, wherein the MPPT control device comprises an MPPT reference voltage generating circuit and an MPPT algorithm basic circuit, and the MPPT reference voltage generating circuit is used for generating a first reference voltage signal for controlling the working point of a solar battery; the MPPT algorithm basic circuit is connected with the MPPT reference voltage generating circuit and a main circuit in the satellite electric propulsion system, and is used for collecting an output voltage signal and an output current signal of the main circuit, generating a control signal according to a second reference voltage signal, the output voltage signal and the output current signal after amplitude limiting processing of the first reference voltage signal, and controlling the MPPT reference voltage generating circuit through the control signal. The invention can realize the energy balance of the satellite electric propulsion system in the illumination period, the shadow period and the whole service life, realize the maximum utilization of energy, maintain the bus voltage in a certain range and ensure the high reliability and stable operation of the satellite power supply system.

Description

MPPT control device, method and equipment applied to satellite electric propulsion system
Technical Field
The invention relates to the technical field of control of satellite electric propulsion systems, in particular to an MPPT control device, method and equipment applied to a satellite electric propulsion system.
Background
The electric propulsion technology is increasingly widely applied to various satellites, wherein the Hall electric propulsion technology has high specific impulse, large thrust and good comprehensive performance, and is the most widely applied electric propulsion technology at present.
In the hall electric propulsion technology, a power supply processing unit is the key of the whole system. The Power processing unit often adopts a solar cell array to supply Power, and an MPPT (Maximum Power Point Tracking) regulation mode is used to improve the utilization rate of the solar cell array and reduce the area of the solar cell array.
In the traditional maximum power point tracking topology, a converter is connected in series at the output end of a solar cell array to realize maximum power tracking of the solar cell array. However, the energy storage inductor in the series MPPT architecture causes slow system dynamic response, and also causes large system loss and difficulty in improving efficiency due to the addition of the reactance element and the power device.
The MPPT technology applied to the Hall electric propulsion system adopts a parallel sequential switch shunt maximum power regulator, a main error amplification signal in the sequential switch shunt regulator is improved to a real-time change value from a fixed voltage reference point, and the change value is given by an MPPT circuit, so that maximum power tracking is indirectly realized.
In actual operation, the voltage of the solar cell array is unstable. When the illumination is sufficient and the temperature is high, the open-circuit voltage of the solar cell array is reduced, the maximum power point voltage is low and may be lower than the bus voltage requirement range, and the input condition of the rear-stage power supply controller is not met; when the light is insufficient and the temperature is low, the open-circuit voltage of the solar cell array is increased, the maximum power point voltage is high, and when the load is light, the output voltage of the solar cell array is quite high and is close to the open-circuit voltage, so that the rear-stage power supply controller can be damaged.
Therefore, the MPPT technology applied to the hall electric propulsion system needs to realize energy balance in an illumination period, a shadow period and the whole service life, realize maximum utilization of energy, maintain bus voltage within a certain range and ensure high reliability and stable operation of a satellite power supply system, but at present, an MPPT control device and a corresponding control method capable of realizing the purpose are lacked.
Disclosure of Invention
The present invention is directed to solving, at least to some extent, one of the technical problems in the related art. Therefore, a first object of the present invention is to provide an MPPT control apparatus applied to a satellite electric propulsion system, so as to achieve energy balance of the satellite electric propulsion system during an illumination period, a shadow period, and a whole life period, to achieve maximum utilization of energy, and to maintain bus voltage within a certain range, thereby ensuring high reliability and stable operation of a satellite power supply system.
A second object of the present invention is to provide an MPPT control method applied to a satellite electric propulsion system.
A third object of the present invention is to provide an MPPT control apparatus.
In order to achieve the purpose, the invention is realized by the following technical scheme:
an MPPT control device for a satellite electric propulsion system, comprising:
the MPPT reference voltage generating circuit is used for generating a first reference voltage signal for controlling the working point of the solar battery;
the MPPT algorithm basic circuit is respectively connected with the MPPT reference voltage generating circuit and a main circuit in a satellite electric propulsion system, and is used for acquiring an output voltage signal and an output current signal of the main circuit, generating a control signal according to a second reference voltage signal after amplitude limiting processing of the first reference voltage signal, the output voltage signal and the output current signal, and controlling the MPPT reference voltage generating circuit through the control signal.
Optionally, the MPPT reference voltage generating circuit includes:
the first end of the first resistor is connected with the output end of the MPPT algorithm basic circuit, the first ends of the second resistor and the fourth resistor are connected with an external low-voltage power supply, and the second end of the third resistor is grounded;
a base electrode of the triode is connected with the second end of the first resistor, a collector electrode of the triode is connected with the second end of the second resistor, and an emitting electrode of the triode is respectively connected with the first ends of the third resistor and the fifth resistor;
the cathode of the first diode is connected with the second end of the fifth resistor, the cathode of the second diode is respectively connected with the anode of the first diode and the second end of the fourth resistor, and the anode of the second diode is grounded;
and a first end of the first capacitor is connected with a second end of the fifth resistor, the second end of the first capacitor is grounded, and the first end of the first capacitor is used for outputting the first reference voltage signal.
Optionally, the MPPT control apparatus applied to the satellite electric propulsion system further includes: the MPPT output amplitude limiting circuit is respectively connected with the MPPT reference voltage generating circuit and the MPPT algorithm basic circuit, and the MPPT output amplitude limiting circuit is used for carrying out amplitude limiting processing on the first reference voltage signal to generate a second reference voltage signal and outputting the second reference voltage signal to the MPPT algorithm basic circuit.
Optionally, the MPPT output limiter circuit includes:
a second capacitor;
the first ends of the sixth resistor and the tenth resistor are connected with an external low-voltage power supply, the seventh resistor is connected with the second capacitor in parallel, the first end of the seventh resistor is connected with the second end of the sixth resistor, and the second end of the seventh resistor is grounded;
the anodes of the third diode, the fourth diode and the fifth diode are all connected with the second end of the tenth resistor;
the positive end of the first operational amplifier is connected with the first end of the first capacitor, the negative end of the first operational amplifier is connected with the cathode of the fourth diode through the eighth resistor, and the output end of the first operational amplifier is connected with the cathode of the third diode;
and the positive end of the second operational amplifier is respectively connected with the second end of the sixth resistor and the first end of the seventh resistor, the negative end of the second operational amplifier is connected with the cathode of the fourth diode through the ninth resistor, and the output end of the second operational amplifier is connected with the cathode of the fifth diode.
Optionally, the MPPT algorithm base circuit includes a sample-and-hold sub-circuit, and the sample-and-hold sub-circuit includes:
the voltage sampling unit is connected with the main circuit and comprises an eleventh resistor, a twelfth resistor, a first MOS (metal oxide semiconductor) transistor and a third capacitor, wherein the first end of the eleventh resistor is connected with the voltage output end of the main circuit, the second end of the eleventh resistor is connected with the first end of the twelfth resistor and the drain electrode of the first MOS transistor, the source electrode of the first MOS transistor is connected with the first end of the third capacitor, the gate electrode of the first MOS transistor is connected with the first output end of the MPPT algorithm basic circuit, and the twelfth resistor and the second end of the third capacitor are grounded;
the current sampling unit is connected with the main circuit and comprises a thirteenth resistor, a fourteenth resistor, a second MOS (metal oxide semiconductor) tube and a fourth capacitor, wherein the first end of the thirteenth resistor is connected with the current output end of the main circuit, the second end of the thirteenth resistor is connected with the first end of the fourteenth resistor and the drain electrode of the second MOS tube, the source electrode of the second MOS tube is connected with the first end of the fourth capacitor, the grid electrode of the second MOS tube is connected with the second output end of the MPPT algorithm basic circuit, and the second end of the fourteenth resistor and the second end of the fourth capacitor are grounded.
Optionally, the MPPT algorithm base circuit further includes a comparison sub-circuit, and the comparison sub-circuit includes:
a positive terminal of the first comparator is connected with the first end of the eleventh resistor, and a negative terminal of the first comparator is connected with the first end of the third capacitor;
a positive terminal of the second comparator is connected with the first terminal of the thirteenth resistor, and a negative terminal of the second comparator is connected with the first terminal of the fourth capacitor;
the MPPT output amplitude limiting circuit comprises a third comparator and a fourth comparator, wherein the positive end of the third comparator and the negative end of the fourth comparator are both connected with the output end of the MPPT output amplitude limiting circuit, the negative end of the third comparator and the positive end of the fourth comparator respectively input a first threshold value and a second threshold value, and the second threshold value is larger than the first threshold value.
Optionally, the MPPT algorithm base circuit further includes a trigger circuit, and the trigger circuit includes:
a first and sub-circuit, a first input terminal of the first and sub-circuit being connected to the output terminal of the first comparator, a second input terminal of the first and sub-circuit being connected to the output terminal of the third comparator;
a second and sub-circuit, a first input terminal of the second and sub-circuit being connected to an output terminal of the second comparator, a second input terminal of the second and sub-circuit being connected to an output terminal of the fourth comparator;
the first input end of the first NAND sub-circuit is connected with the output end of the first NAND sub-circuit, the second input end of the first NAND sub-circuit is connected with the output end of the second NAND sub-circuit, the first input end of the second NAND sub-circuit is connected with the output end of the first NAND sub-circuit, and the second input end of the second NAND sub-circuit is connected with the output end of the second NAND sub-circuit.
Optionally, the second diode is a zener diode.
In order to achieve the above object, a second aspect of the present invention provides an MPPT control method applied to a satellite electric propulsion system, the method including:
generating a first reference voltage signal for controlling the working point of the solar cell, and carrying out amplitude limiting processing on the first reference voltage signal to generate a second reference voltage signal;
and acquiring an output voltage signal and an output current signal of a main circuit, generating a control signal according to the second reference voltage signal, the output voltage signal and the output current signal, and controlling the MPPT reference voltage generation circuit through the control signal so as to adjust the first reference voltage signal.
In order to achieve the above object, a third aspect of the present invention provides an MPPT control apparatus including the above MPPT control device applied to a satellite electric propulsion system.
The invention has at least the following technical effects:
the MPPT algorithm basic circuit samples a voltage signal and a current signal which are output by a main circuit and used for tracking the first reference voltage signal, generates a control signal according to the sampled voltage signal, current signal and second reference voltage signal, and controls the MPPT reference voltage generating circuit in real time through the control signal to enable a charging capacitor and a charging resistor in the MPPT reference voltage generating circuit to be charged and discharged, so that the real-time regulation of the first reference voltage signal is realized, and the satellite electric propulsion system is in a lighting period, And the energy in the shadow period and the whole service life is balanced, the maximum utilization of the energy is realized, and the bus voltage is maintained within a certain range from the second aspect, so that the high reliability and the stable operation of the satellite power supply system are ensured.
Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.
Drawings
Fig. 1 is a block diagram of an MPPT control apparatus applied to a satellite electric propulsion system according to an embodiment of the present invention;
fig. 2 is a schematic circuit diagram of an MPPT reference voltage generating circuit according to an embodiment of the present invention;
fig. 3 is a block diagram of an MPPT control apparatus applied to a satellite electric propulsion system according to another embodiment of the present invention;
fig. 4 is a schematic diagram of an MPPT output limiter circuit according to an embodiment of the present invention;
FIG. 5 is a schematic diagram of a basic MPPT algorithm circuit according to an embodiment of the present invention;
fig. 6 is a flowchart of an MPPT control method applied to a satellite electric propulsion system according to an embodiment of the present invention;
fig. 7 is a block diagram of an MPPT control apparatus according to an embodiment of the present invention.
Detailed Description
Reference will now be made in detail to the present embodiments, examples of which are illustrated in the accompanying drawings, wherein like reference numerals refer to the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are illustrative and intended to explain the present invention and should not be construed as limiting the present invention.
The MPPT control apparatus, method, and device applied to the satellite electric propulsion system of the present embodiment are described below with reference to the accompanying drawings.
Fig. 1 is a block diagram of an MPPT control apparatus applied to a satellite electric propulsion system according to an embodiment of the present invention. As shown in fig. 1, an MPPT control device 1 applied to a satellite electric propulsion system includes an MPPT reference voltage generation circuit 10 and an MPPT algorithm base circuit 20.
The MPPT reference voltage generating circuit is used for generating a first reference voltage signal for controlling the working point of the solar cell; the MPPT algorithm base circuit is respectively connected with the MPPT reference voltage generating circuit and a main circuit in the satellite electric propulsion system, and is used for acquiring an output voltage signal and an output current signal of the main circuit, generating a control signal according to a second reference voltage signal, the output voltage signal and the output current signal after amplitude limiting processing of the first reference voltage signal, and controlling the MPPT reference voltage generating circuit through the control signal.
In this embodiment, in an initial state, the MPPT reference voltage generating circuit 10 generates a first reference voltage signal Vmppt for controlling the solar cell operating point to approach the maximum power point continuously, and after performing amplitude limiting processing on the first reference voltage signal Vmppt, inputs a second reference voltage signal Vmppt _ ref after the amplitude limiting processing to the MPPT algorithm base circuit 20. The MPPT algorithm base circuit 20 further samples an output voltage signal and an output current signal of a main control circuit controlled by the MPPT control device 1, which are mainly used for tracking the first reference voltage signal Vmppt, wherein the first reference voltage signal Vmppt is in positive correlation and negative correlation with the output voltage signal and the output current signal, respectively. The MPPT algorithm base circuit 20 generates a control signal according to the second reference voltage signal Vmppt _ ref, the output voltage signal, and the output current signal to control the MPPT reference voltage generating circuit 10, thereby realizing real-time adjustment of the first reference voltage signal Vmppt, further realizing energy balance of the satellite electric propulsion system in an illumination period, a shadow period, and a whole life period, realizing maximum utilization of energy, and maintaining the bus voltage within a certain range to ensure high reliability and stable operation of the satellite power supply system.
As shown in fig. 2, the MPPT reference voltage generating circuit 10 includes: first to fifth resistors R 1 ～R 5 A triode, a first diode D 1 A second diode D 2 And a first capacitor C 1 。
Wherein the first resistor R 1 Is connected to the output of the MPPT algorithm base circuit 20, and a second resistor R 2 And a fourth resistor R 4 Is connected with an external low-voltage power supply VCC, and a third resistor R 3 The second terminal of (1) is grounded; base electrode and first resistor R of triode 1 Is connected with the second end of the triode, and the collector of the triode is connected with a second resistor R 2 Is connected with the second end of the triode, and the emitting electrodes of the triode are respectively connected with a third resistor R 3 And a fifth resistor R 5 Is connected with the first end of the first connecting pipe; first diode D 1 Cathode and fifth resistor R 5 Is connected to a second terminal of a second diode D 2 Respectively with the first diode D 1 And a fourth resistor R 4 Is connected to a second terminal of a second diode D 2 The anode of (2) is grounded; a first capacitor C 1 First terminal and fifth resistor R 5 Is connected to the first capacitor C 1 Is grounded, and a first capacitor C 1 Is used for outputting the first reference voltage signal Vmppt.
In this embodiment, the fifth resistor R 5 And a first capacitor C 1 A charging resistor, a charging capacitor and a second diode D 2 Is a zener diode. As shown in the figure 2 of the drawings,
Figure BDA0003719327900000071
is the output signal of MPPT algorithm base circuit 20, i.e., the control signal. If it is not
Figure BDA0003719327900000072
At a high level, the first capacitor C 1 Charging; if it is not
Figure BDA0003719327900000073
At low level, the first capacitor C 1 Discharging through a triode. In this example, the fifth resistor R 5 And a first capacitor C 1 The value of (b) determines the oscillation frequency of the MPPT system. When the load power demand is small, the system is not operating in the MPPT mode,
Figure BDA0003719327900000074
at low level, the first capacitor C 1 Discharge to a minimum through the triode. This minimum is provided by a zener diode, i.e., a second diode D 2 The steady voltage value of (2) is determined. At this time, the bus voltage is regulated to a fixed voltage, i.e., the regulated voltage value, and the satellite electric propulsion system operates in a constant voltage mode.
As shown in fig. 3, the MPPT control apparatus 1 applied to the satellite electric propulsion system further includes an MPPT output limiter circuit 30. The MPPT output limiter circuit 30 is connected to the MPPT reference voltage generator 10 and the MPPT algorithm base circuit 20, respectively, and the MPPT output limiter circuit 30 is configured to perform a limiting process on the first reference voltage signal Vmppt to generate a second reference voltage signal Vmppt _ ref, and output the second reference voltage signal Vmppt _ ref to the MPPT algorithm base circuit 20.
As shown in fig. 4, the MPPT output limiter circuit 30 includes: second capacitor C 2 Sixth to tenth resistors R 6 ～R 10 A third to a fifth diode D 3 ～D 5 A first operational amplifier M1 and a second operational amplifier M2.
Wherein, the sixth resistor R 6 And a tenth resistance R 10 A first terminal connected with an external low-voltage power supply VCC, a seventh resistor R 7 And a second capacitor C 2 Parallel connection, a seventh resistor R 7 First terminal and sixth resistor R 6 Is connected to the second terminal of the seventh resistor R 7 The second terminal of (a) is grounded; third diode D 3 A fourth diode D 4 And a fifth diode D 5 Is connected with a tenth resistor R 10 Is connected with the second end of the first end; the positive terminal of the first operational amplifier M1 and the first capacitor C 1 Is connected to the first terminal of the first operational amplifier M1, the negative terminal of the first operational amplifier M1 is connected through an eighth resistor R 8 And a fourth diode D 4 Is connected to the cathode ofThe output terminal of the operational amplifier M1 and the third diode D 3 The cathode of (a) is connected; the positive terminal of the second operational amplifier M2 and the sixth resistor R 6 Second terminal and seventh resistor R 7 Is connected to the first terminal of the second operational amplifier M2, the negative terminal of the second operational amplifier M2 is connected through a ninth resistor R 9 And a fourth diode D 4 Is connected to the cathode of the second operational amplifier M2, and the output of the second operational amplifier M2 is connected to the fifth diode D 5 Is connected to the cathode.
In this embodiment, the MPPT reference voltage generating circuit 10 outputs the first reference voltage signal Vmppt to the MPPT output limiter circuit 30. Where Vhigh _ ref is the upper limit of the system output voltage, and this value is decremented by the value of Vmppt after passing through the follower circuit of M2 and the value of Vmppt after passing through the follower circuit of M1. When Vmppt is less than Vhigh _ ref, the MPPT output limiting circuit 30 outputs a value Vmppt _ ref equal to Vmppt; when Vmppt exceeds Vhigh _ ref, the MPPT output limiting circuit 30 outputs a value Vmppt _ ref equal to the voltage upper limit value Vhigh _ ref.
As shown in fig. 5, MPPT algorithm base circuit 20 includes a sample-and-hold sub-circuit 21, and sample-and-hold sub-circuit 21 includes: the device comprises a voltage sampling unit and a current sampling unit.
Wherein, the voltage sampling unit is connected with the main circuit and comprises an eleventh resistor R 11 And a twelfth resistor R 12 A first MOS transistor T1 and a third capacitor C 3 Wherein, an eleventh resistor R 11 Is connected with the voltage output end of the main circuit, and an eleventh resistor R 11 Second terminal and a twelfth resistor R 12 Is connected to the drain of the first MOS transistor T1, the source of the first MOS transistor T1 is connected to the third capacitor C 3 Is connected to the first terminal of the MPPT algorithm base circuit 20, the gate of the first MOS transistor T1 is connected to the first output terminal of the MPPT algorithm base circuit 20
Figure BDA0003719327900000081
A control signal output terminal connected to a twelfth resistor R 12 And a third capacitance C 3 The second terminal of (a) is grounded.
In this embodiment, the current sampling unit is connected to the main circuit, and the current sampling unit includes a thirteenth resistor R 13 A fourteenth resistor R 14 A second MOS transistor T2 and a fourth capacitor C 4 Wherein, a thirteenth resistor R 13 Is connected with the current output end of the main circuit, and a thirteenth resistor R 13 Second terminal and a fourteenth resistor R 14 Is connected to the drain of the second MOS transistor T2, the source of the second MOS transistor T2 is connected to the fourth capacitor C 4 Is connected to the first terminal of the MPPT algorithm base circuit 20, the gate of the second MOS transistor T2 is connected to the second output terminal of the MPPT algorithm base circuit 20, and the fourteenth resistor R is connected to the second output terminal of the MPPT algorithm base circuit 14 And a fourth capacitance C 4 The second terminal of (a) is grounded.
With continued reference to fig. 5, the MPPT algorithm base circuit 20 further includes a comparison sub-circuit 22, wherein the comparison sub-circuit 22 includes: a first comparator COMP1, a second comparator COMP2, a third comparator COMP3 and a fourth comparator COMP 4.
Wherein, the positive terminal of the first comparator COMP1 and the eleventh resistor R 11 Is connected to the first terminal of the first comparator COMP1, the negative terminal of the first comparator COMP1 and the third capacitor C 3 Is connected with the first end of the first connecting pipe; the positive terminal of the second comparator COMP2 and a thirteenth resistor R 13 Is connected to the first terminal of the second comparator COMP2, the negative terminal of the second comparator COMP2 and the fourth capacitor C 4 Is connected with the first end of the first connecting pipe; a positive terminal of the third comparator COMP3 and a negative terminal of the fourth comparator COMP4 are both connected to an output terminal of the MPPT output clipping circuit 30, and a negative terminal of the third comparator COMP3 and a positive terminal of the fourth comparator COMP4 respectively input a first threshold value Vlow _ threshold and a second threshold value Vhigh _ threshold, wherein the second threshold value Vhigh _ threshold is greater than the first threshold value Vlow _ threshold.
With continued reference to fig. 5, the MPPT algorithm base circuit 20 further includes a flip-flop circuit 23, where the flip-flop circuit 23 includes: the first and sub-circuit Y1, the second and sub-circuit Y2, the first nand sub-circuit Y3, and the second nand sub-circuit Y4.
A first input end of the first and sub-circuit Y1 is connected to an output end of the first comparator COMP1, and a second input end of the first and sub-circuit Y1 is connected to an output end of the third comparator COMP 3; a first input terminal of the second and sub-circuit Y2 is connected to an output terminal of the second comparator COMP2, and a second input terminal of the second and sub-circuit Y2 is connected to an output terminal of the fourth comparator COMP 4; a first input terminal of the first nand sub-circuit Y3 is connected to an output terminal of the first and sub-circuit Y1, a second input terminal of the first nand sub-circuit Y3 is connected to an output terminal of the second nand sub-circuit Y4, a first input terminal of the second nand sub-circuit Y4 is connected to an output terminal of the first nand sub-circuit Y3, and a second input terminal of the second nand sub-circuit Y4 is connected to an output terminal of the second and sub-circuit Y2.
As shown in fig. 6, the present invention further provides an MPPT control method applied to a satellite electric propulsion system, the method being applied to the MPPT control device applied to a satellite electric propulsion system, the method including:
step S1: generating a first reference voltage signal for controlling the working point of the solar cell, and carrying out amplitude limiting processing on the first reference voltage signal to generate a second reference voltage signal;
step S2: and acquiring an output voltage signal and an output current signal of the main circuit, generating a control signal according to the second reference voltage signal, the output voltage signal and the output current signal, and controlling the MPPT reference voltage generation circuit through the control signal so as to adjust the first reference voltage signal.
As an example, the whole operation cycle of the system may be divided into to T4 periods according to the illumination period and the shadow period, where the power-on initial time T0, T1 and T2 are all turned off, so that the first comparator COMP1 and the second comparator COMP2 both output a high level, Reset1 is 1, and Set1 is 1; initial second reference voltage signal Vmppt _ ref ≦ Vlow _ threshold ≦ Vhigh _ threshold, Reset2 ═ 0, Set2 ═ 1, when Reset ═ 0, Set ═ 1, Q ═ 0, control signal Vmppt _ ref, control signal vmset, and Set _ threshold, and control signal Q, when Set is greater than or equal to 0, and the initial second reference voltage signal Vmppt _ ref is greater than or equal to the initial second reference voltage signal Set, and the initial second reference voltage signal Set is greater than or equal to the initial second reference voltage signal Set, and is greater than or equal to the initial second reference voltage signal Set, and is greater than or equal to the initial voltage signal Set, and is greater than or equal to 0, and is equal to the Set2, and is equal to 0, and is equal to the initial value
Figure BDA0003719327900000101
Figure BDA0003719327900000102
By R 5 And C 1 Charging is performed, and the first reference voltage signal Vmppt rapidly rises.
In the period from t0 to t1, the second reference voltage signal Vmppt _ ref is ≦ Vlow _ threshold, Q is 0,
Figure BDA0003719327900000103
due to the fact that
Figure BDA0003719327900000104
T1 is on and the first capacitor C 1 Charging is performed, the first comparator COMP1 outputs a high level, Reset1 is 1; since Q is 0, T2 is turned off, and the second capacitor C 2 The voltage value at the previous time is kept at 0, the second comparator COMP2 outputs a high level, Set1 is equal to 1, and the second reference voltage signal Vmppt _ ref is equal to Vlow _ threshold until time t 1.
In the time period from t1 to t2, the second reference voltage signal Vmppt _ ref > Vlow _ threshold, Reset2 is equal to 1, Set2 is equal to 1, at which time Reset is equal to 1, Set is equal to 1, the state of the flip-flop remains unchanged, the control signal Q is equal to 1, Vmppt _ ref continues to increase until time t2, Vmppt _ ref is equal to Vhigh _ threshold.
In the time period from t2 to t3, Vmpt _ ref is not greater than Vhigh _ threshold due to voltage disturbance; at time t2, Vmppt _ ref is Vhigh _ threshold, Reset2 is 1, Set2 is 0, at this time, Reset is 1, Set is 0, Q is 1, Q is 0, the voltage value Vmppt _ ref decreases, Vsa also decreases accordingly, that is, the positive terminal voltage of the first comparator COMP1 decreases continuously. In the time period from T2 to T3, since Q is 1, T2 is turned on, and the second capacitor C 2 Charging is performed, and the second comparator COMP2 outputs a high level; due to the fact that
Figure BDA0003719327900000105
T1 is turned off and the first capacitor C 1 kV' sa at time t2, i.e. the voltage of the negative terminal of the first comparator COMP1, remains unchanged until time t3, the positive terminal is less than or equal to the negative terminal, the output of the first comparator COMP1 is 0, Reset is 0, Set is 1,
Figure BDA0003719327900000106
q is 0 and the Vmppt _ ref voltage value rises again.
During the time period t2 to t3, a current disturbance is generated.
At time t3, because
Figure BDA0003719327900000107
Q is 0, T2 is off, and the second capacitor C 2 Keeping the kI ' sa at the time t3, regarding the second comparator COMP2, the positive terminal is Isa, the negative terminal is kI ' sa at the time t3, since Isa continuously decreases, Isa is less than or equal to kI ' sa, the positive terminal is less than or equal to the negative terminal, the output of the second comparator COMP2 is 0, and Set is 0.
In the time period from t3 to t4, Set is 0, Reset is 0, and control signals
Figure BDA0003719327900000108
Keeping the voltage value of Vmppt _ ref at 1, increasing Vsa and increasing the voltage of the positive terminal of the first comparator COMP 1; as can be seen from the solar array characteristic curve, Isa continuously decreases, i.e., the voltage of the positive terminal of the second comparator COMP2 continuously decreases.
At time t4, the positive terminal of the second comparator COMP2 is less than or equal to the negative terminal, the output of the second comparator COMP2 is 0, Set is 0, Reset is 1, Q is 1,
Figure BDA0003719327900000111
and a new round of voltage disturbance is started after the time t4, then current disturbance is carried out, the operation point of the solar array continuously approaches the maximum power point, and the solar array vibrates in a small range near the maximum power point after being disturbed in a staggered mode for a plurality of times, so that the energy balance of the satellite electric propulsion system in an illumination period, a shadow period and the whole service life can be realized, the maximum utilization of the energy is realized, the bus voltage can be controlled within a certain range through real-time regulation of the first reference voltage, and the high reliability and stable operation of the satellite power supply system can be further ensured.
Further, the invention also provides MPPT control equipment. As shown in fig. 7, the MPPT control apparatus 100 includes the MPPT control device 1 applied to the satellite electric propulsion system described above.
In summary, the MPPT reference voltage generating circuit generates a first reference voltage signal for controlling the solar cell operating point to approach the maximum power point continuously, performs amplitude limiting processing on the first reference voltage signal to control the bus voltage within a certain range from the first aspect, and feeds back a second reference voltage signal after the amplitude limiting processing to the MPPT algorithm base circuit, where the MPPT algorithm base circuit samples the voltage signal and the current signal output by the main circuit and used for tracking the first reference voltage signal, generates a control signal according to the sampled voltage signal, current signal and second reference voltage signal, and controls the MPPT reference voltage generating circuit in real time through the control signal to charge and discharge the charging capacitor and the charging resistor in the MPPT reference voltage generating circuit, thereby realizing real-time adjustment of the first reference voltage signal, and realizing that the satellite electric propulsion system is in the illumination period, The energy balance in the shadow period and the whole service life period realizes the maximum utilization of the energy, and maintains the bus voltage in a certain range from the second aspect, thereby ensuring the high reliability and stable operation of the satellite power supply system.
It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.
While the present invention has been described in detail with reference to the preferred embodiments, it should be understood that the above description should not be taken as limiting the invention. Various modifications and alterations to this invention will become apparent to those skilled in the art upon reading the foregoing description. Accordingly, the scope of the invention should be determined from the following claims.

Claims (10)

1. An MPPT control device for a satellite electric propulsion system, comprising:
the MPPT reference voltage generating circuit is used for generating a first reference voltage signal for controlling the working point of the solar battery;
the MPPT algorithm basic circuit is respectively connected with the MPPT reference voltage generating circuit and a main circuit in a satellite electric propulsion system, and is used for acquiring an output voltage signal and an output current signal of the main circuit, generating a control signal according to a second reference voltage signal after amplitude limiting processing of the first reference voltage signal, the output voltage signal and the output current signal, and controlling the MPPT reference voltage generating circuit through the control signal.
2. The MPPT control device for a satellite electric propulsion system of claim 1, wherein the MPPT reference voltage generating circuit includes:
the first end of the first resistor is connected with the output end of the MPPT algorithm basic circuit, the first ends of the second resistor and the fourth resistor are connected with an external low-voltage power supply, and the second end of the third resistor is grounded;
a base electrode of the triode is connected with the second end of the first resistor, a collector electrode of the triode is connected with the second end of the second resistor, and an emitting electrode of the triode is respectively connected with the first ends of the third resistor and the fifth resistor;
the cathode of the first diode is connected with the second end of the fifth resistor, the cathode of the second diode is respectively connected with the anode of the first diode and the second end of the fourth resistor, and the anode of the second diode is grounded;
and a first end of the first capacitor is connected with a second end of the fifth resistor, the second end of the first capacitor is grounded, and the first end of the first capacitor is used for outputting the first reference voltage signal.
3. The MPPT control device for a satellite electric propulsion system of claim 2, further comprising:
the MPPT output amplitude limiting circuit is respectively connected with the MPPT reference voltage generating circuit and the MPPT algorithm basic circuit, and the MPPT output amplitude limiting circuit is used for carrying out amplitude limiting processing on the first reference voltage signal to generate a second reference voltage signal and outputting the second reference voltage signal to the MPPT algorithm basic circuit.
4. The MPPT control system for a satellite electric propulsion system of claim 3, wherein the MPPT output limiter circuit includes:
a second capacitor;
the first ends of the sixth resistor and the tenth resistor are connected with an external low-voltage power supply, the seventh resistor is connected with the second capacitor in parallel, the first end of the seventh resistor is connected with the second end of the sixth resistor, and the second end of the seventh resistor is grounded;
anodes of the third diode, the fourth diode and the fifth diode are all connected with the second end of the tenth resistor;
the positive end of the first operational amplifier is connected with the first end of the first capacitor, the negative end of the first operational amplifier is connected with the cathode of the fourth diode through the eighth resistor, and the output end of the first operational amplifier is connected with the cathode of the third diode;
and the positive end of the second operational amplifier is respectively connected with the second end of the sixth resistor and the first end of the seventh resistor, the negative end of the second operational amplifier is connected with the cathode of the fourth diode through the ninth resistor, and the output end of the second operational amplifier is connected with the cathode of the fifth diode.
5. The MPPT control device applied to a satellite electric propulsion system of claim 4, wherein the MPPT algorithm base circuit includes a sample-and-hold sub-circuit including:
the voltage sampling unit is connected with the main circuit and comprises an eleventh resistor, a twelfth resistor, a first MOS (metal oxide semiconductor) tube and a third capacitor, wherein the first end of the eleventh resistor is connected with the voltage output end of the main circuit, the second end of the eleventh resistor is connected with the first end of the twelfth resistor and the drain electrode of the first MOS tube, the source electrode of the first MOS tube is connected with the first end of the third capacitor, the gate electrode of the first MOS tube is connected with the first output end of the MPPT algorithm basic circuit, and the twelfth resistor and the second end of the third capacitor are grounded;
the current sampling unit is connected with the main circuit and comprises a thirteenth resistor, a fourteenth resistor, a second MOS (metal oxide semiconductor) tube and a fourth capacitor, wherein the first end of the thirteenth resistor is connected with the current output end of the main circuit, the second end of the thirteenth resistor is connected with the first end of the fourteenth resistor and the drain electrode of the second MOS tube, the source electrode of the second MOS tube is connected with the first end of the fourth capacitor, the grid electrode of the second MOS tube is connected with the second output end of the MPPT algorithm basic circuit, and the second end of the fourteenth resistor and the second end of the fourth capacitor are grounded.
6. The MPPT control device for a satellite electric propulsion system of claim 5, wherein the MPPT algorithm base circuit further includes a comparison sub-circuit, the comparison sub-circuit including:
a positive terminal of the first comparator is connected with the first end of the eleventh resistor, and a negative terminal of the first comparator is connected with the first end of the third capacitor;
a positive terminal of the second comparator is connected with the first terminal of the thirteenth resistor, and a negative terminal of the second comparator is connected with the first terminal of the fourth capacitor;
the MPPT output amplitude limiting circuit comprises a third comparator and a fourth comparator, wherein the positive end of the third comparator and the negative end of the fourth comparator are both connected with the output end of the MPPT output amplitude limiting circuit, the negative end of the third comparator and the positive end of the fourth comparator respectively input a first threshold value and a second threshold value, and the second threshold value is larger than the first threshold value.
7. The MPPT control device for a satellite electric propulsion system of claim 6, wherein the MPPT algorithm base circuit further includes a trigger circuit, the trigger circuit including:
a first and sub-circuit, a first input terminal of the first and sub-circuit being connected to the output terminal of the first comparator, a second input terminal of the first and sub-circuit being connected to the output terminal of the third comparator;
a second and sub-circuit, a first input terminal of the second and sub-circuit being connected to the output terminal of the second comparator, a second input terminal of the second and sub-circuit being connected to the output terminal of the fourth comparator;
the first input end of the first NAND sub-circuit is connected with the output end of the first NAND sub-circuit, the second input end of the first NAND sub-circuit is connected with the output end of the second NAND sub-circuit, the first input end of the second NAND sub-circuit is connected with the output end of the first NAND sub-circuit, and the second input end of the second NAND sub-circuit is connected with the output end of the second NAND sub-circuit.
8. The MPPT control system for a satellite electric propulsion system of claim 2, wherein the second diode is a zener diode.
9. MPPT control method for satellite electric propulsion systems, based on an MPPT control device for satellite electric propulsion systems according to any of claims 1 to 8, characterized in that it comprises:
generating a first reference voltage signal for controlling the working point of the solar cell, and carrying out amplitude limiting processing on the first reference voltage signal to generate a second reference voltage signal;
and acquiring an output voltage signal and an output current signal of a main circuit, generating a control signal according to the second reference voltage signal, the output voltage signal and the output current signal, and controlling the MPPT reference voltage generation circuit through the control signal so as to adjust the first reference voltage signal.
10. An MPPT control device, characterized by comprising an MPPT control device applied to a satellite electric propulsion system as claimed in any one of claims 1 to 8.
CN202210755005.XA 2022-06-29 2022-06-29 MPPT control device, method and equipment applied to satellite electric propulsion system Pending CN114977462A (en)

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