CN113746337B - Power supply device of spacecraft, power supply controller of spacecraft and control method - Google Patents
Power supply device of spacecraft, power supply controller of spacecraft and control method Download PDFInfo
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- CN113746337B CN113746337B CN202110863435.9A CN202110863435A CN113746337B CN 113746337 B CN113746337 B CN 113746337B CN 202110863435 A CN202110863435 A CN 202110863435A CN 113746337 B CN113746337 B CN 113746337B
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02M—APPARATUS FOR CONVERSION BETWEEN AC AND AC, BETWEEN AC AND DC, OR BETWEEN DC AND DC, AND FOR USE WITH MAINS OR SIMILAR POWER SUPPLY SYSTEMS; CONVERSION OF DC OR AC INPUT POWER INTO SURGE OUTPUT POWER; CONTROL OR REGULATION THEREOF
- H02M3/00—Conversion of dc power input into dc power output
- H02M3/02—Conversion of dc power input into dc power output without intermediate conversion into ac
- H02M3/04—Conversion of dc power input into dc power output without intermediate conversion into ac by static converters
- H02M3/10—Conversion of dc power input into dc power output without intermediate conversion into ac by static converters using discharge tubes with control electrode or semiconductor devices with control electrode
- H02M3/145—Conversion of dc power input into dc power output without intermediate conversion into ac by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal
- H02M3/155—Conversion of dc power input into dc power output without intermediate conversion into ac by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only
- H02M3/156—Conversion of dc power input into dc power output without intermediate conversion into ac by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only with automatic control of output voltage or current, e.g. switching regulators
- H02M3/158—Conversion of dc power input into dc power output without intermediate conversion into ac by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only with automatic control of output voltage or current, e.g. switching regulators including plural semiconductor devices as final control devices for a single load
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- 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
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02M—APPARATUS FOR CONVERSION BETWEEN AC AND AC, BETWEEN AC AND DC, OR BETWEEN DC AND DC, AND FOR USE WITH MAINS OR SIMILAR POWER SUPPLY SYSTEMS; CONVERSION OF DC OR AC INPUT POWER INTO SURGE OUTPUT POWER; CONTROL OR REGULATION THEREOF
- H02M3/00—Conversion of dc power input into dc power output
- H02M3/02—Conversion of dc power input into dc power output without intermediate conversion into ac
- H02M3/04—Conversion of dc power input into dc power output without intermediate conversion into ac by static converters
- H02M3/10—Conversion of dc power input into dc power output without intermediate conversion into ac by static converters using discharge tubes with control electrode or semiconductor devices with control electrode
- H02M3/145—Conversion of dc power input into dc power output without intermediate conversion into ac by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal
- H02M3/155—Conversion of dc power input into dc power output without intermediate conversion into ac by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only
- H02M3/156—Conversion of dc power input into dc power output without intermediate conversion into ac by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only with automatic control of output voltage or current, e.g. switching regulators
- H02M3/158—Conversion of dc power input into dc power output without intermediate conversion into ac by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only with automatic control of output voltage or current, e.g. switching regulators including plural semiconductor devices as final control devices for a single load
- H02M3/1582—Buck-boost converters
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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
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/50—Photovoltaic [PV] energy
- Y02E10/56—Power conversion systems, e.g. maximum power point trackers
Abstract
The invention provides a power supply device of a spacecraft, a power supply controller of the spacecraft and a control method, wherein the power supply device comprises a front-stage MPPT circuit and a rear-stage S3R circuit, the front-stage MPPT circuit is connected with the rear-stage S3R circuit, the rear-stage S3R circuit is used for realizing a shunt regulation function, the power supply device has two working states of an MPPT working mode and a shunt regulation mode, has the function of autonomously switching the MPPT mode and the S3R mode, and can actively switch to the S3R mode to transmit the front-stage output power to a bus while ensuring the maximum power output. The beneficial effects of the invention are as follows: the power supply device has the function of autonomously switching the MPPT mode and the S3R mode, does not need to increase a post-stage converter, and has the advantages of high utilization rate of solar battery conversion electric energy and high power transfer efficiency.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to a power supply device of a spacecraft, a power supply controller of the spacecraft and a control method.
Background
The topology of a spacecraft energy system can be divided from an energy transfer perspective into a direct energy transfer mode (DET) and a peak power tracking mode (PPT). The S3R topological structure in the direct energy transmission mode has wide application due to the characteristics of simplicity, reliability, high efficiency and the like. In the peak power tracking mode, an MPPT topology is most often used to improve the output power utilization rate of the solar cell.
The S3R topological structure, also called a sequential switch shunt regulator (The Sequential Switching Shunt Regulator), has the advantages that the solar cell array power is directly transmitted to a load, the power transmission efficiency is high, and the redundant energy is shunted through the shunt regulator SR. The solar cell array has the defects that the maximum power output cannot be realized due to the adoption of the direct energy transmission system by the current divider, the utilization rate of the output power of the solar cell array is low, and the solar cell has to leave enough margin in the initial design stage, so that the weight and the volume of the whole star are increased.
The MPPT topological structure is also called maximum power tracking (maximum power point tracking, MPPT), and the working point of the solar battery is regulated in real time through a control strategy to always work near the optimal power point, so that the power supply system outputs more energy under the condition of the same solar battery configuration. Compared with the S3R architecture, the MPPT architecture has lower power transmission efficiency due to the fact that the switching regulator is connected in series, but can track the maximum power output point of the solar cell array at any time, and maximally utilizes the electric energy converted by the solar cell.
In order to improve the MPPT efficiency, some battery-less system full-adjustment architectures also use DET circuits to implement MPPT. For example, a sequential switching shunt maximum power regulator (S3 MPR) architecture is mainly characterized by: the main error amplified signal (MEA) in the traditional sequential switching shunt regulator (S3R) topological structure is improved from a fixed voltage reference point to a value which changes in real time, and the change value is given by an MPPT circuit, so that the maximum power tracking is realized. Compared with the MPPT topological structure of the fully-regulated bus, the topology reduces the loss of the power converter on the power transmission line and is beneficial to maximally utilizing the output power of the solar cell array. However, compared with the traditional S3R circuit, the bus voltage is not fixed any more, but is controlled by the MPPT module to realize maximum power tracking by changing the bus voltage, so that the change range of the output voltage of the current divider is larger, the post-stage DCDC converter is required to be added to realize full-regulation of the voltage-stabilizing bus, the system volume is definitely increased, and the overall efficiency is lower.
Disclosure of Invention
In order to solve the architecture drawbacks in the background art, the present invention provides a power supply device (MPS 3R for short) of a spacecraft.
The invention provides a power supply device of a spacecraft, which comprises a front-stage MPPT circuit and a rear-stage S3R circuit, wherein the front-stage MPPT circuit is connected with the rear-stage S3R circuit, the rear-stage S3R circuit is used for realizing a shunt regulation function, the power supply device has two working states of an MPPT working mode and a shunt regulation mode, has the function of autonomously switching the MPPT mode and the S3R mode, and can actively switch to the S3R mode to transmit the front-stage output power to a bus while ensuring the maximum power output.
The invention further improves, including the first module and second module, the said first module includes MPPT module, judging module, first field effect tube enhancement type N-MOS, second field effect tube enhancement type N-MOS, third field effect tube enhancement type N-MOS, fourth field effect tube enhancement type N-MOS, first diode, second diode, third diode, fourth diode, electric capacity, first inductance, the said judging module couples to said MPPT module, the source of the said first field effect tube enhancement type N-MOS couples to one end of the first inductance, the drain of the said first field effect tube enhancement type N-MOS couples to one end of the electric capacity, the said another end of the first inductance couples to fourth diode, the said first diode one end couples to source of the said first field effect tube enhancement type N-MOS, the another end of the said first diode couples to drain of the said first field effect tube enhancement type N-MOS; the source electrode of the second field effect tube enhanced N-MOS is grounded, the drain electrode of the second field effect tube enhanced N-MOS is connected with the source electrode of the first field effect tube enhanced N-MOS, one end of the second diode is connected with the source electrode of the second field effect tube enhanced N-MOS, and the other end of the second diode is connected with the drain electrode of the second field effect tube enhanced N-MOS; the source electrode of the third field effect tube enhanced N-MOS is grounded, the drain electrode of the third field effect tube enhanced N-MOS is connected between the first inductor and the fourth diode, one end of the third diode is connected with the source electrode of the third field effect tube enhanced N-MOS, and the other end of the third diode is connected with the drain electrode of the third field effect tube enhanced N-MOS; the drain electrode of the fourth field effect transistor enhanced N-MOS is connected with the capacitor, the source electrode of the fourth field effect transistor enhanced N-MOS is grounded, and the source electrode of the fourth field effect transistor enhanced N-MOS is connected with the MPPT module;
the second module is connected with the first module, the second module comprises a fifth field effect tube enhanced N-MOS, a fifth diode, a second inductor and a sixth diode, a source electrode of the fifth field effect tube enhanced N-MOS is connected with one end of the second inductor, the other end of the second inductor is connected with the sixth diode, a drain electrode of the fifth field effect tube enhanced N-MOS is connected with the second module, one end of the sixth diode is connected with the source electrode of the fifth field effect tube enhanced N-MOS, and the other end of the sixth diode is connected with the drain electrode of the fifth field effect tube enhanced N-MOS.
The invention also provides a spacecraft power supply controller, which comprises the power supply device, wherein the power supply device is adopted to design a solar cell array power regulator according to power requirements, and the power regulator is used for regulating the power of a solar cell array in the illumination period and charging a storage battery, so that the MPPT function before track transfer is realized, and the shunting regulation function is realized after track transfer.
As a further improvement of the invention, the synchronous Buck and the power supply device are adopted, the output power of the solar cell array is regulated in the illumination period, the storage battery is charged, the MPPT+synchronous Buck function before track transfer is realized by using a single converter, and the shunt regulation function is realized after track transfer.
As a further improvement of the invention, the electric propulsion operation before orbit transfer is performed, the spacecraft power supply controller defaults to BUCK operation, when the electric propulsion is effective, the MPPT control keeps the solar cell sailboard to work at the maximum power, and the whole power supply controller works at the maximum power point, so that the effective energy supply is ensured.
As a further improvement of the present invention, an FSBB and a power supply device are employed, the FSBB enabling a bi-directional flow of input and output power.
As a further improvement of the invention, the FSBB comprises a first switch tube, a second switch tube, a third switch tube, a fourth switch tube, an inductor, a first capacitor and a second capacitor, wherein the source electrode of the first switch tube is connected with the drain electrode of the second switch tube, the drain electrode of the first switch tube is connected with one end of the first capacitor, and the source electrode of the second switch tube is connected with the other end of the first capacitor; the third switching tube source electrode is connected with the fourth switching tube drain electrode, the third switching tube drain electrode is connected with one end of the second capacitor, the fourth switching tube source electrode is respectively connected with the other end of the second capacitor and the second switching tube source electrode, one end of the inductor is connected between the first switching tube and the second switching tube, and the other end of the inductor is connected between the third switching tube and the fourth switching tube.
When Vin > Vo, the BUCK mode is operated, and the third switching tube is turned on for a long time, so that the first switching tube and the second switching tube complete the BUCK conversion function; when Vin is approximately equal to Vo, the voltage conversion function is completed when the voltage conversion circuit works in a Buck-Boost mode, and at the moment, the first switching tube, the second switching tube, the third switching tube and the fourth switching tube work; when Vin < Vo, the Boost mode is operated, the first switching tube is long-pass, and the third switching tube and the fourth switching tube complete the Boost conversion function.
The invention also provides a control method based on the spacecraft power supply controller, wherein the power supply device works in a DC/DC power supply conversion state before the spacecraft runs on a transfer orbit, when the bus power is smaller than the sum of the sailboard energy and the battery charging current, the power supply device is controlled by the MEA to stabilize the bus voltage, and at the moment, the battery is charged according to the set current gear; when the bus load is gradually increased until the bus power is larger than the sum of the energy of the sailboard and the battery charging current, the power supply device enters an MPPT mode, the maximum capacity of the sailboard is used as the load to supply energy, and the battery charging current is controlled by the MEA; as the bus load increases further, the battery will change from a charged state to a discharged state to meet the load demand;
when the spacecraft runs on the transfer orbit, the power supply device realizes the switching between the DC/DC converter and the S3R circuit under the control of the bus conversion instruction, and the circuit control logic is as follows: when the bus power is smaller than the sum of the sailboard energy and the battery charging current, the power supply device is controlled by the MEA to work in a sequential shunt regulation mode, at the moment, the MPS3R module realizes bus stability, and the battery is charged according to the set current gear; when the bus load is gradually increased until the bus power is larger than the sum of the sailboard energy and the battery charging current, the power supply device enters a full power supply mode, and the battery charging current is controlled by the MEA; as the bus load further increases, the battery will change from a charged state to a discharged state to meet the load demand.
The beneficial effects of the invention are as follows: the power supply device has the function of autonomously switching the MPPT mode and the S3R mode, does not need to increase a post-stage converter, and has the advantages of high utilization rate of solar battery conversion electric energy and high power transfer efficiency.
Drawings
FIG. 1 is a schematic block diagram of MPS 3R;
FIG. 2 is a synchronous Buck topology;
fig. 3 (a) is an MPPT operation mode diagram of the inductive charging phase;
fig. 3 (b) is an MPPT operation mode diagram of the inductance discharging part;
FIG. 4 (a) is a shunt regulator operating mode diagram of the power stage;
FIG. 4 (b) is a split-flow conditioning operating mode diagram of the split-flow phase;
FIG. 5 is a block diagram of a four-switch Buck-Boost topology;
fig. 6 is a block diagram of the fsbb+mps3r circuit structure.
Detailed Description
The invention discloses a power supply device (MPS 3R for short) of a spacecraft, wherein the MPS3R is designed by adding an S3R circuit (a front MPPT+a rear S3R circuit for short) capable of being actively switched on the basis of a fully-regulated MPPT scheme, so that the maximum power output is ensured, and meanwhile, the MPS3R circuit can be actively switched to an S3R mode to efficiently transmit the power of the front stage to a bus. The S3R shunt regulating circuit part can be compatible with various S3R architectures, for example, a BOOST type S3R design form is adopted.
As shown in fig. 1, a power supply device (MPS 3R) of the present invention includes a first module and a second module, where the first module includes an MPPT module, a judging module, a first fet enhancement N-MOSV1, a second fet enhancement N-MOSV2, a third fet enhancement N-MOSV3, a fourth fet enhancement N-MOSV5, a first diode D1, a second diode D2, a third diode D3, a fourth diode V4, a capacitor Cin, and a first inductor L1, the judging module is connected to the MPPT module, a source of the first fet enhancement N-MOSV1 is connected to one end of the first inductor L1, a drain of the first fet enhancement N-MOSV1 is connected to one end of the capacitor Cin, another end of the first inductor L1 is connected to the fourth diode V4, one end of the first diode D1 is connected to the first fet enhancement N-MOSV1, and another end of the first diode D1 is connected to the drain of the first fet enhancement N-MOSV 1; the source electrode of the second field effect tube enhanced N-MOSV2 is grounded, the drain electrode of the second field effect tube enhanced N-MOSV2 is connected with the source electrode of the first field effect tube enhanced N-MOSV1, one end of the second diode D2 is connected with the source electrode of the second field effect tube enhanced N-MOSV2, and the other end of the second diode D2 is connected with the drain electrode of the second field effect tube enhanced N-MOSV 2; the source electrode of the third field effect tube enhanced N-MOSV3 is grounded, the drain electrode of the third field effect tube enhanced N-MOSV3 is connected between the first inductor L1 and the fourth diode V4, one end of the third diode D3 is connected with the source electrode of the third field effect tube enhanced N-MOSV3, and the other end of the third diode D3 is connected with the drain electrode of the third field effect tube enhanced N-MOSV 3; the drain electrode of the fourth field effect tube enhanced N-MOSV5 is connected with the capacitor Cin, the source electrode of the fourth field effect tube enhanced N-MOSV5 is grounded, and the source electrode of the fourth field effect tube enhanced N-MOSV5 is connected with the MPPT module;
the second module is connected with the first module, the second module comprises a fifth field effect tube enhanced N-MOSV6, a fifth diode D4, a second inductor L2 and a sixth diode D5, a source electrode of the fifth field effect tube enhanced N-MOSV6 is connected with one end of the second inductor L2, the other end of the second inductor L2 is connected with the sixth diode D5, a drain electrode of the fifth field effect tube enhanced N-MOSV6 is connected with the second module, one end of the sixth diode D5 is connected with the source electrode of the fifth field effect tube enhanced N-MOSV6, and the other end of the sixth diode D5 is connected with the drain electrode of the fifth field effect tube enhanced N-MOSV 6.
For example, the MPS3R circuit structure is used for designing a solar cell array power regulator according to power requirements in the design of a spacecraft power supply controller (PCU), and is used for regulating the power of a solar cell array in the illumination period and charging a storage battery, so that the MPPT function before track transfer is realized, and the shunt regulation function is realized after track transfer.
The MPS3R architecture integral control strategy adopts domain control, and ensures the bus voltage to realize the bus voltage stabilization through a unified main error amplifier.
As in the above-mentioned spacecraft power controller PCU application, before the spacecraft runs on the transfer orbit, MPS3R works in the DC/DC power conversion state, when the bus power is smaller than the sum of the sailboard energy and the battery charging current, MPS3R is controlled by MEA to stabilize the bus voltage, and at this time, the battery is charged according to the set current gear. When the bus load is gradually increased until the bus power is larger than the sum of the sailboard energy and the battery charging current, MPS3R enters an MPPT mode, the maximum capacity of the sailboard is used as the load to supply energy, and the battery charging current is controlled by the MEA; as the bus load further increases, the battery will change from a charged state to a discharged state to meet the load demand.
When the spacecraft runs on the transfer orbit, the MPS3R realizes the switching between the DC/DC converter and the S3R circuit under the control of a bus conversion instruction, and the circuit control logic is as follows: when the bus power is smaller than the sum of the sailboard energy and the battery charging current, the MPS3R is controlled by the MEA to work in a sequential shunt regulation mode, and at the moment, the MPS3R realizes bus stability, and the battery is charged according to the set current gear. When the bus load is gradually increased until the bus power is larger than the sum of the sailboard energy and the battery charging current, the MPS3R enters a full power supply mode, and the battery charging current is controlled by the MEA; as the bus load further increases, the battery will change from a charged state to a discharged state to meet the load demand.
MPS3R architecture implementation form:
the MPS3R architecture may be implemented with a variety of (without limitation to) power conversion topologies, with two circuit implementations illustrated as follows:
synchronous Buck+MPS3R circuit: by adopting the PCU design of the all-electric-propulsion spacecraft with the synchronous Buck+MPS3R circuit, the output power of the solar cell array is regulated and the storage battery is charged in the illumination period, and the topology can realize the MPPT+synchronous Buck function before track transfer by using only a single converter and realize the shunt regulation function after track transfer. The circuit block diagram is shown in fig. 2.
The electric propulsion operation before track transfer is performed, the PCU defaults to BUCK operation, and V3 and V6 are disconnected at the moment, and V1 and V2 are controlled by MEA signals. When the electric propulsion is effective, the MPPT control keeps the solar panel sailboard working at the maximum power, the V5 is closed, the whole power supply controller works at the maximum power point, and the effective energy supply is ensured, as shown in fig. 3 (a) and 3 (b).
And after the track transfer is completed, the star service executes switching operation, and the star service sends an MPPT_INH (MPPT inhibition, S3R mode) instruction to the PCU to autonomously judge the current working state. The hardware circuit operates to close V1, open V2, and unlock V3, V6 from pull-down. The shunt regulator is controlled by the MEA, V5 is disconnected to ensure that the input capacitance does not cause additional losses in the shunt, and at this time the overall power supply controller is consistent with the conventional S3R regulation, ensuring an efficient supply of energy to the bus, as shown in fig. 4 (a) and 4 (b).
FSBB+MPS3R circuit: the four-switch Buck-Boost (FSBB) topology can realize the functions of Buck (Buck circuit), boost (Boost topology) and Buck-Boost (Boost-Boost topology), and compared with the function of simply cascading the Buck topology and the Boost topology together to finish the Boost-Buck, the FSBB circuit has fewer devices and higher efficiency. The topology is shown in fig. 5.
The working principle of the FSBB topology is simply analyzed as follows: the scheme is four-switch buck-boost topology, and can realize bidirectional flow of input and output power. The switching of input and output voltage can be realized by controlling the change of the duty ratio of the switching tube, the scheme is divided into three working modes, 1) when Vin > Vo, the BUCK mode is operated, at the moment, the third switching tube Q3 is long-ended, and the first switching tube Q1 and the second switching tube Q2 complete the BUCK conversion function; 2) When Vin is approximately equal to Vo, the voltage conversion circuit works in a Buck-Boost mode, and at the moment, the first switching tube Q1, the second switching tube Q2, the third switching tube Q3 and the fourth switching tube Q4 work to complete a voltage conversion function; 3) When Vin < Vo, the Boost mode is operated, and the first switching tube Q1 is long-pass, and the third switching tube Q3 and the fourth switching tube Q4 complete the Boost conversion function.
The FSBB+MPS3R circuit structure is shown in fig. 6, the volume can be reduced in a magnetic coupling mode, and by combining the characteristics of the MPS3R structure, one switching tube in the FSBB topology can have a shunt tube function at the same time, so that the volume reduction and the power density improvement are realized.
The invention has the technical advantages that:
1. the MPPT working mode and the shunt regulating mode can be simultaneously provided without additionally adding a converter. And the S3R mode can be actively switched to transmit the output power of the front stage to the bus at high efficiency while ensuring the maximum power output.
2. Compared with a full-regulation bus MPPT architecture, the power transfer efficiency can be improved through a rear-stage S3R circuit while the electric energy converted by the solar battery is utilized to the maximum extent; compared with the traditional S3R architecture, the maximum power tracking can be realized by changing the bus voltage under the control of the front-stage MPPT, and the energy utilization rate is improved. Compared with an S3MPR architecture, the power secondary conversion of the post-stage DCDC converter is not needed, so that the power density of the system is improved.
3. And the method can be compatible with various power conversion topologies, and can use fewer devices compared with a two-topology cascading mode, so that the power conversion efficiency is improved.
The foregoing is a further detailed description of the invention in connection with the preferred embodiments, and it is not intended that the invention be limited to the specific embodiments described. It will be apparent to those skilled in the art that several simple deductions or substitutions may be made without departing from the spirit of the invention, and these should be considered to be within the scope of the invention.
Claims (8)
1. The power supply device of the spacecraft is characterized by comprising a front-stage MPPT circuit and a rear-stage S3R circuit, wherein the front-stage MPPT circuit is connected with the rear-stage S3R circuit, the rear-stage S3R circuit is used for realizing a shunt regulation function, the power supply device has two working states of an MPPT working mode and a shunt regulation mode, has the function of autonomously switching the MPPT mode and the S3R mode, and can actively switch to the S3R mode to transmit the front-stage output power to a bus while ensuring the maximum power output; the MPPT system comprises a first module and a second module, wherein the first module comprises an MPPT module, a judging module, a first field effect tube enhancement type N-MOS (V1), a second field effect tube enhancement type N-MOS (V2), a third field effect tube enhancement type N-MOS (V3), a fourth field effect tube enhancement type N-MOS (V5), a first diode (D1), a second diode (D2), a third diode (D3), a fourth diode (V4), a capacitor (Cin) and a first inductor (L1), the judging module is connected with the MPPT module, the source electrode of the first field effect tube enhancement type N-MOS (V1) is connected with one end of the first inductor (L1), the drain electrode of the first field effect tube enhancement type N-MOS (V1) is connected with one end of the capacitor (Cin), the other end of the first inductor (L1) is connected with the fourth diode (V4), one end of the first diode (D1) is connected with the first field effect tube enhancement type N-MOS (V1), and the other end of the first field effect tube enhancement type N-MOS (V1) is connected with the drain electrode of the first diode (V1); the source electrode of the second field effect tube enhanced N-MOS (V2) is grounded, the drain electrode of the second field effect tube enhanced N-MOS (V2) is connected with the source electrode of the first field effect tube enhanced N-MOS (V1), one end of the second diode (D2) is connected with the source electrode of the second field effect tube enhanced N-MOS (V2), and the other end of the second diode (D2) is connected with the drain electrode of the second field effect tube enhanced N-MOS (V2); the source electrode of the third field effect tube enhanced N-MOS (V3) is grounded, the drain electrode of the third field effect tube enhanced N-MOS (V3) is connected between the first inductor (L1) and the fourth diode (V4), one end of the third diode (D3) is connected with the source electrode of the third field effect tube enhanced N-MOS (V3), and the other end of the third diode (D3) is connected with the drain electrode of the third field effect tube enhanced N-MOS (V3); the drain electrode of the fourth field effect transistor enhanced N-MOS (V5) is connected with the capacitor (Cin), the source electrode of the fourth field effect transistor enhanced N-MOS (V5) is grounded, and the source electrode of the fourth field effect transistor enhanced N-MOS (V5) is connected with the MPPT module;
the second module is connected with the first module, the second module comprises a fifth field effect tube enhanced N-MOS (V6), a fifth diode (D4), a second inductor (L2) and a sixth diode (D5), a source electrode of the fifth field effect tube enhanced N-MOS (V6) is connected with one end of the second inductor (L2), the other end of the second inductor (L2) is connected with the sixth diode (D5), a drain electrode of the fifth field effect tube enhanced N-MOS (V6) is connected with the second module, one end of the sixth diode (D5) is connected with a source electrode of the fifth field effect tube enhanced N-MOS (V6), and the other end of the sixth diode (D5) is connected with a drain electrode of the fifth field effect tube enhanced N-MOS (V6).
2. The power supply controller of the spacecraft is characterized by comprising the power supply device according to claim 1, wherein the power supply device is used for designing a solar cell array power regulator according to power requirements and is used for regulating the power of a solar cell array in an illumination period and charging a storage battery, so that an MPPT function before track transfer is realized, and a shunt regulating function is realized after track transfer.
3. The spacecraft power controller according to claim 2, wherein a synchronous Buck and power supply device are adopted, output power of the solar cell array is regulated during illumination period, a storage battery is charged, a single converter is used for realizing an mppt+synchronous Buck function before track transfer, a shunt regulation function is realized after track transfer, and Buck represents a step-down circuit.
4. A spacecraft power controller as claimed in claim 3, wherein the spacecraft power controller defaults to BUCK operation when the electric propulsion is in effect, the MPPT control keeps the solar panel operating at maximum power, the whole power controller operating at maximum power point, ensuring efficient energy supply.
5. The spacecraft power controller of claim 2, wherein the FSBB enables bi-directional flow of input and output power using the FSBB and a power supply device.
6. The spacecraft power controller according to claim 5, wherein the FSBB comprises a first switching tube (Q1), a second switching tube (Q2), a third switching tube (Q3), a fourth switching tube (Q4), an inductor (L), a first capacitor and a second capacitor, wherein a source of the first switching tube (Q1) is connected to a drain of the second switching tube (Q2), a drain of the first switching tube (Q1) is connected to one end of the first capacitor, and a source of the second switching tube (Q2) is connected to the other end of the first capacitor; the source electrode of the third switching tube (Q3) is connected with the drain electrode of the fourth switching tube (Q4), the drain electrode of the third switching tube (Q3) is connected with one end of the second capacitor, the source electrode of the fourth switching tube (Q4) is respectively connected with the other end of the second capacitor and the source electrode of the second switching tube (Q2), one end of the inductor (L) is connected between the first switching tube (Q1) and the second switching tube (Q2), and the other end of the inductor (L) is connected between the third switching tube (Q3) and the fourth switching tube (Q4).
7. The spacecraft power controller according to claim 6, wherein when Vin > Vo, the BUCK mode is operated, wherein the third switching tube (Q3) is long-circuited, and the first switching tube (Q1) and the second switching tube (Q2) perform a BUCK conversion function; when Vin is approximately equal to Vo, the voltage conversion circuit works in a Buck-Boost mode, and at the moment, the first switching tube (Q1), the second switching tube (Q2), the third switching tube (Q3) and the fourth switching tube (Q4) work to finish the voltage conversion function; when Vin < Vo, the Boost-type switching device works in a Boost mode, and at the moment, the first switching tube (Q1) is long-turned on, and the third switching tube (Q3) and the fourth switching tube (Q4) complete a Boost conversion function.
8. A control method based on a spacecraft power controller according to any one of claims 2-7, characterized in that the power supply device is operated in a DC/DC power conversion state before the spacecraft is operated in a transfer orbit, when the bus power is smaller than the sum of the sailboard energy and the battery charging current, the power supply device is controlled by the MEA to stabilize the bus voltage, and at this time, the battery is charged according to the set current gear; when the bus load is gradually increased until the bus power is larger than the sum of the energy of the sailboard and the battery charging current, the power supply device enters an MPPT mode, the maximum capacity of the sailboard is used as the load to supply energy, and the battery charging current is controlled by the MEA; as the bus load increases further, the battery will change from a charged state to a discharged state to meet the load demand;
when the spacecraft runs on the transfer orbit, the power supply device realizes the switching between the DC/DC converter and the S3R circuit under the control of the bus conversion instruction, and the circuit control logic is as follows: when the bus power is smaller than the sum of the sailboard energy and the battery charging current, the power supply device is controlled by the MEA to work in a sequential shunt regulation mode, at the moment, the MPS3R module realizes bus stability, and the battery is charged according to the set current gear; when the bus load is gradually increased until the bus power is larger than the sum of the sailboard energy and the battery charging current, the power supply device enters a full power supply mode, and the battery charging current is controlled by the MEA; as the bus load further increases, the battery will change from a charged state to a discharged state to meet the load demand.
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| CN106647920A (en) * | 2016-12-23 | 2017-05-10 | 山东航天电子技术研究所 | Satellite power controller |
| CN112994211A (en) * | 2021-03-30 | 2021-06-18 | 上海空间电源研究所 | High-efficiency space power energy transmission system |
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| CN106647920A (en) * | 2016-12-23 | 2017-05-10 | 山东航天电子技术研究所 | Satellite power controller |
| CN112994211A (en) * | 2021-03-30 | 2021-06-18 | 上海空间电源研究所 | High-efficiency space power energy transmission system |
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