CN113746337A - 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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- CN113746337A CN113746337A CN202110863435.9A CN202110863435A CN113746337A CN 113746337 A CN113746337 A CN 113746337A CN 202110863435 A CN202110863435 A CN 202110863435A CN 113746337 A CN113746337 A CN 113746337A
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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
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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 be actively switched to the S3R mode to transmit front-stage output power to a bus while ensuring maximum power output. The invention has the beneficial effects that: the power supply device has the functions of autonomously switching the MPPT mode and the S3R mode, does not need to add a post converter, and has the advantages of high electric energy utilization rate of solar battery conversion and high power transmission efficiency.
Description
Technical Field
The invention relates to the technical field of spaceflight, 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 into a direct energy transfer mode (DET) and a peak power tracking mode (PPT) from the perspective of energy transfer. The S3R topological structure in the direct energy transfer mode has wide application due to the characteristics of simplicity, reliability, high efficiency and the like. In the peak power tracking method, the MPPT topology is most often used to improve the output power utilization of the solar cell.
The S3R topology, also called Sequential Switching Shunt Regulator (The Sequential Switching Shunt Regulator), has The advantages of transferring solar array power to load directly, having high power transfer efficiency, and shunting excess energy through The Shunt Regulator SR. The solar cell array power divider has the advantages that the power divider adopts a direct energy transmission system, so that the output of a solar cell cannot realize the maximum power output, the utilization rate of the output power of the solar cell array is low, sufficient margin is required to be reserved at the initial design stage of the solar cell, and the weight and the volume of the whole satellite are increased.
The MPPT topology, also called Maximum Power Point Tracking (MPPT), adjusts the operating point of the solar cell in real time through a control strategy so that the solar cell always operates near the optimal power point, so that the power supply system outputs more energy under the same solar cell configuration condition. Compared with the structure of S3R, the MPPT structure has a lower power transfer efficiency due to the series connection of the switching regulator, but can track the maximum power output point of the solar cell array at any time and maximally utilize the electric energy converted by the solar cell.
In order to improve MPPT efficiency, in some batteryless system full-regulation architectures, the MPPT is also implemented by using a DET circuit. For example, the sequential switching shunt maximum power regulator (S3MPR) architecture is mainly characterized in that: the main error amplification signal (MEA) in the topology structure of the traditional sequential switching shunt regulator (S3R) 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 the maximum power tracking is realized. Compared with the MPPT topological structure of the full-regulating bus, the topology reduces the loss of a power converter on a power transmission line and is beneficial to utilizing the output power of the solar cell array to the maximum extent. 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 the output voltage of the shunt has a wide variation range, a post-stage DCDC converter needs to be added to realize full regulation of the regulated bus, the system volume is increased undoubtedly, and the overall efficiency is low.
Disclosure of Invention
In order to solve the architectural shortcomings in the background art, the present invention provides a power supply device (MPS3R for short) for 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 be actively switched to the S3R mode to transmit front-stage output power to a bus while ensuring maximum power output.
As a further improvement of the invention, the device comprises a first module and a second module, wherein the first module comprises an MPPT module, a judging module, a first field effect transistor enhanced N-MOS, a second field effect transistor enhanced N-MOS, a third field effect transistor enhanced N-MOS, a fourth field effect transistor enhanced N-MOS, a first diode, a second diode, a third diode, a fourth diode, a capacitor and a first inductor, the judging module is connected with the MPPT module, the source electrode of the first field effect transistor enhanced N-MOS is connected with one end of a first inductor, the drain electrode of the first field effect transistor enhanced N-MOS is connected with one end of a capacitor, the other end of the first inductor is connected with a fourth diode, one end of the first diode is connected with the source electrode of the first field effect transistor enhanced N-MOS, the other end of the first diode is connected with the drain electrode of the first field effect transistor enhanced N-MOS; the source electrode of the second field effect transistor enhanced N-MOS is grounded, the drain electrode of the second field effect transistor enhanced N-MOS is connected with the source electrode of the first field effect transistor enhanced N-MOS, one end of a second diode is connected with the source electrode of the second field effect transistor enhanced N-MOS, and the other end of the second diode is connected with the drain electrode of the second field effect transistor enhanced N-MOS; the source electrode of the third field effect transistor enhanced N-MOS is grounded, the drain electrode of the third field effect transistor 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 transistor enhanced N-MOS, and the other end of the third diode is connected with the drain electrode of the third field effect transistor 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 and comprises a fifth field effect transistor enhanced N-MOS, a fifth diode, a second inductor and a sixth diode, the source electrode of the fifth field effect transistor 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, the drain electrode of the fifth field effect transistor 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 transistor enhanced N-MOS, and the other end of the sixth diode is connected with the drain electrode of the fifth field effect transistor enhanced N-MOS.
The invention also provides a spacecraft power controller which comprises the power supply device, wherein the power supply device is adopted to design the solar cell array power regulator according to the power requirement, is used for power regulation of the solar cell array in the illumination period and storage battery charging, realizes the MPPT function before orbit transfer, and realizes the shunt regulation function after the orbit transfer.
As a further improvement of the invention, a synchronous Buck and a power supply device are adopted to regulate the output power of the solar cell array and charge a storage battery in the illumination period, a single converter is used for realizing the functions of MPPT (maximum power point tracking) and synchronous Buck before track transfer and shunting regulation after track transfer.
As a further improvement of the invention, the electric propulsion works before the orbit transfer, the spacecraft power controller defaults that the BUCK works in the shunt regulation part, when the electric propulsion takes effect, the MPPT controls and keeps the solar battery sailboard to work at the maximum power point, and the whole power controller works at the maximum power point, thereby ensuring the effective supply of energy.
As a further improvement of the invention, an FSBB and a power supply device are adopted, and the FSBB can realize bidirectional flow of input and output power.
As a further improvement of the present invention, the FSBB includes 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 a source of the first switch tube is connected to a drain of the second switch tube, a drain of the first switch tube is connected to one end of the first capacitor, and a source of the second switch tube is connected to the other end of the first capacitor; the source electrode of the third switch tube is connected with the drain electrode of the fourth switch tube, the drain electrode of the third switch tube is connected with one end of the second capacitor, the source electrode of the fourth switch tube is respectively connected with the other end of the second capacitor and the source electrode of the second switch tube, one end of the inductor is connected between the first switch tube and the second switch tube, and the other end of the inductor is connected between the third switch tube and the fourth switch tube.
As a further improvement of the invention, when Vin > Vo, the BUCK mode is operated, at the moment, the third switch tube is long-passed, and the first switch tube and the second switch tube complete the voltage reduction conversion function; when Vin is approximately equal to Vo, the Buck-Boost mode is adopted, and at the moment, the first switch tube, the second switch tube, the third switch tube and the fourth switch tube all work to complete the voltage conversion function; when Vin is less than Vo, the converter works in a Boost mode, at the moment, the first switching tube is in long-pass state, and the third switching tube and the fourth switching tube complete a Boost conversion function.
The invention also provides a control method based on the spacecraft power supply controller, before the spacecraft operates on the transfer orbit, the power supply device works in a DC/DC power supply conversion state, when the bus power is less than the sum of sailboard energy and 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 load of the bus is gradually increased until the power of the bus is greater than the sum of the energy of the sailboard and the charging current of the battery, the power supply device enters an MPPT mode, the maximum capacity of the sailboard is used as the load to supply energy, and the charging current of the battery 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 a transfer orbit, the power supply device realizes the switching between the DC/DC converter and the S3R circuit under the control of a bus conversion instruction, and the control logic of the circuit is as follows: when the power of the bus is less than the sum of the energy of the sailboard and the charging current of the battery, the power supply device is controlled by the MEA to work in a sequential shunt regulation mode, at the moment, the MPS3R module realizes the stability of the bus, and the battery is charged according to the set current gear; when the load of the bus is gradually increased until the power of the bus is greater than the sum of the energy of the sailboard and the charging current of the battery, the power supply device enters a full power supply mode, and the charging current of the battery 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.
The invention has the beneficial effects that: the power supply device has the functions of autonomously switching the MPPT mode and the S3R mode, does not need to add a post converter, and has the advantages of high electric energy utilization rate of solar battery conversion and high power transmission efficiency.
Drawings
Fig. 1 is a functional block diagram of MPS 3R;
FIG. 2 is a synchronous Buck topology;
figure 3(a) is a diagram of MPPT operating mode during the inductive charging phase;
FIG. 3(b) is a diagram of MPPT mode of operation of the inductive discharge section;
FIG. 4(a) is a diagram of a shunt regulation mode of operation during a power supply phase;
FIG. 4(b) is a diagram of a split-flow modulation mode of operation during the split-flow phase;
FIG. 5 is a four-switch Buck-Boost topology structure;
fig. 6 is a block diagram of the circuit configuration of FSBB + MPS 3R.
Detailed Description
The invention discloses a power supply device (MPS3R for short) of a spacecraft, and the MPS3R is designed by adding an S3R circuit (a front-stage MPPT + a rear-stage S3R circuit, MPS3R for short) which can be actively switched on the basis of a full-regulation type MPPT scheme, so that the maximum power output is ensured, and meanwhile, the power of the front stage can be actively switched to an S3R mode to efficiently transmit the power of the front stage to a bus. The S3R shunt regulation circuit part is compatible with various S3R architectures, such as S3R design form of BOOST type.
As shown in fig. 1, the power supply apparatus (MPS3R) of the present invention includes a first module and a second module, the first module includes an MPPT module, a determination module, a first fet-enhanced N-MOSV1, a second fet-enhanced N-MOSV2, a third fet-enhanced N-MOSV3, a fourth fet-enhanced N-MOSV5, a first diode D1, a second diode D2, a third diode D3, a fourth diode V4, a capacitor Cin, a first inductor L1, the determination module is connected to the MPPT module, a source of the first fet-enhanced N-MOSV1 is connected to one end of a first inductor L1, a drain of the first fet-enhanced N-MOSV1 is connected to one end of the capacitor Cin, the other end of the first inductor L1 is connected to the fourth diode V4, one end of the first diode D1 is connected to a source of the first fet-enhanced N-MOSV1, the other end of the first diode D1 is connected with the drain electrode of the first field effect transistor enhanced N-MOSV 1; the source electrode of the second field effect transistor enhanced N-MOSV2 is grounded, the drain electrode of the second field effect transistor enhanced N-MOSV2 is connected with the source electrode of the first field effect transistor enhanced N-MOSV1, one end of a second diode D2 is connected with the source electrode of the second field effect transistor enhanced N-MOSV2, and the other end of the second diode D2 is connected with the drain electrode of the second field effect transistor enhanced N-MOSV 2; the source of the third fet-enhanced N-MOSV3 is grounded, the drain of the third fet-enhanced N-MOSV3 is connected between the first inductor L1 and the fourth diode V4, one end of the third diode D3 is connected to the source of the third fet-enhanced N-MOSV3, and the other end of the third diode D3 is connected to the drain of the third fet-enhanced N-MOSV 3; the drain electrode of the fourth field effect transistor enhanced N-MOSV5 is connected with the capacitor Cin, the source electrode of the fourth field effect transistor enhanced N-MOSV5 is grounded, and the source electrode of the fourth field effect transistor enhanced N-MOSV5 is connected with the MPPT module;
the second module is connected with the first module and comprises a fifth field effect transistor enhanced N-MOSV6, a fifth diode D4, a second inductor L2 and a sixth diode D5, the source of the fifth field effect transistor enhanced N-MOSV6 is connected with one end of a second inductor L2, the other end of the second inductor L2 is connected with a sixth diode D5, the drain of the fifth field effect transistor enhanced N-MOSV6 is connected with the second module, one end of a sixth diode D5 is connected with the source of the fifth field effect transistor enhanced N-MOSV6, and the other end of the sixth diode D5 is connected with the drain of the fifth field effect transistor enhanced N-MOSV 6.
For example, the method is applied to the design of a spacecraft Power Controller (PCU), and the MPS3R circuit structure is adopted to design a solar cell array power regulator according to power requirements, so that the power regulation and storage battery charging of the solar cell array in the illumination period are realized, the MPPT function before orbit transfer is realized, and the shunt regulation function is realized after the orbit transfer.
The MPS3R framework overall control strategy adopts the domain control, and the bus voltage is ensured to realize the bus voltage stability through a unified main error amplifier.
As in the above-described spacecraft power controller PCU application, the MPS3R operates in a DC/DC power conversion state before the spacecraft is operating in orbit, and when the bus power is less than the sum of the windsurfing board energy and the battery charging current, the MPS3R is controlled by the MEA to stabilize the bus voltage, at which time the battery is charged in accordance with the set current notch. When the load of the bus is gradually increased until the bus power is larger than the sum of the energy of the sailboard and the charging current of the battery, MPPT mode is entered by MPPT 3R, the maximum capacity of the sailboard is used as the load to supply energy, and the charging current of the battery is controlled by MEA; as the bus load increases further, the battery will change from a charged state to a discharged state to meet the load demand.
After the spacecraft runs on the transfer orbit, the MPS3R realizes switching between the DC/DC converter and the S3R circuit under the control of the bus switching instruction, and the circuit control logic is: when the bus power is less than the sum of the energy of the sailboard and the charging current of the battery, the MPS3R works in a sequential shunt regulation mode under the control of the MEA, at the moment, the MPS3R realizes the 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 greater than the sum of the energy of the sailboard and the battery charging current, MPS3R enters a full-power-supply mode, and the battery charging current is controlled by MEA; as the bus load increases further, the battery will change from a charged state to a discharged state to meet the load demand.
MPS3R architecture implementation:
the MPS3R architecture can be implemented in compliance with a variety of (not limited to, two circuit implementations as follows):
synchronous Buck + MPS3R circuit: the design of the full-electric propulsion spacecraft PCU with the synchronous Buck + MPS3R circuit is adopted, the output power of the solar battery array is adjusted in the illumination period, the storage battery is charged, the topology can realize the MPPT + synchronous Buck function before orbit transfer by using a single converter, and the shunt adjusting function is realized after the orbit transfer. The circuit block diagram is shown in fig. 2.
Before the track transfer, the electric propulsion works, the PCU works in a shunting regulation part by default to BUCK, and V3 and V6 are disconnected, and V1 and V2 are controlled by an MEA signal. When the electric propulsion is effective, the MPPT control keeps the solar battery sailboard to work at the maximum power point, the V5 is closed, and the whole power supply controller works at the maximum power point, so that the effective energy supply is ensured, as shown in the figure 3(a) and the figure 3 (b).
After the track transfer is completed, the star performs switching operation, and the star sends an MPPT _ INH (MPPT prohibited, S3R mode) instruction to the PCU to autonomously determine the current working state. The hardware circuit operation closes V1, opens V2, and releases the pull-down lock of V3, V6. The shunt regulation section is controlled by the MEA and V5 is opened to ensure that the input capacitance does not cause additional losses in the shunt, while the overall power controller is in accordance with the conventional S3R regulation scheme to ensure efficient power supply 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 a Buck (voltage reduction circuit), a Boost (voltage Boost topology) and a Buck-Boost (voltage Boost topology), and compared with the simple function of cascading the Buck topology and the Boost topology together to complete the voltage Boost and voltage Boost, the FSBB circuit has fewer used devices and higher efficiency. The topology is shown in fig. 5.
The working principle of the FSBB topology is briefly analyzed as follows: the scheme is a four-switch buck-boost topology, and bidirectional flow of input and output power can be realized. The scheme is divided into three working modes, namely 1) when Vin is larger than Vo, the BUCK mode is worked, at the moment, the third switching tube Q3 is on, and the first switching tube Q1 and the second switching tube Q2 complete the voltage reduction conversion function; 2) when Vin is approximately equal to Vo, the Buck-Boost mode is adopted, 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 all work to complete the voltage conversion function; 3) when Vin < Vo, the converter works in a Boost mode, at the moment, the first switching tube Q1 is long-passed, and the third switching tube Q3 and the fourth switching tube Q4 complete a Boost conversion function.
As shown in fig. 6, the FSBB + MPS3R circuit structure can reduce the volume by means of magnetic coupling, and in combination with the characteristics of the MPS3R architecture, one switching tube in the FSBB topology can have the function of a shunt tube, thereby achieving the reduction of the volume and the improvement of the power density.
The technical advantages of the invention are as follows:
1. the MPPT control circuit can have two working states of an MPPT working mode and a shunt regulation mode at the same time without additionally adding a converter. The mode can be actively switched to the S3R mode to efficiently transmit the output power of the front stage to the bus while ensuring the maximum power output.
2. Compared with a full-regulation bus MPPT framework, the power transmission 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 framework, 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 the S3MPR framework, the power density of the system is improved because a post-stage DCDC converter is not required to be added for carrying out power secondary conversion.
3. The power conversion device is compatible with various power conversion topologies, can use fewer devices compared with a two-topology cascade mode, and improves the power conversion efficiency.
The foregoing is a more detailed description of the invention in connection with specific preferred embodiments and it is not intended that the invention be limited to these specific details. For those skilled in the art to which the invention pertains, several simple deductions or substitutions can be made without departing from the spirit of the invention, and all shall be considered as belonging to the protection scope of the invention.
Claims (9)
1. The utility model provides a power supply unit of spacecraft which characterized in that, includes preceding stage MPPT circuit and back stage S3R circuit, preceding stage MPPT circuit with back stage S3R circuit links to each other, back stage S3R circuit is used for realizing shunting regulation function, and this power supply unit has two kinds of operating condition of MPPT mode and shunting regulation mode, has the function of autonomically switching MPPT mode and S3R mode, when guaranteeing maximum power output, can initiatively switch to S3R mode and transmit preceding stage output power to the generating line.
2. The power supply apparatus of claim 1, comprising a first module and a second module, wherein the first module comprises an MPPT module, a determination module, a first FET-enhanced N-MOS (V1), a second FET-enhanced N-MOS (V2), a third FET-enhanced N-MOS (V3), a fourth FET-enhanced N-MOS (V5), a first diode (D1), a second diode (D2), a third diode (D3), a fourth diode (V4), a capacitor (Cin), a first inductor (L1), the determination module is connected to the MPPT module, a source of the first FET-enhanced N-MOS (V1) is connected to one end of the first inductor (L1), a drain of the first FET-enhanced N-MOS (V1) is connected to one end of the capacitor (Cin), the other end of the first inductor (L1) is connected with a fourth diode (V4), one end of the first diode (D1) is connected with the source electrode of the first field effect transistor enhanced N-MOS (V1), and the other end of the first diode (D1) is connected with the drain electrode of the first field effect transistor enhanced N-MOS (V1); the source electrode of the second field effect transistor enhanced N-MOS (V2) is grounded, the drain electrode of the second field effect transistor enhanced N-MOS (V2) is connected with the source electrode of the first field effect transistor enhanced N-MOS (V1), one end of a second diode (D2) is connected with the source electrode of the second field effect transistor enhanced N-MOS (V2), and the other end of the second diode (D2) is connected with the drain electrode of the second field effect transistor enhanced N-MOS (V2); the source of the third FET-enhanced N-MOS (V3) is grounded, the drain of the third FET-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 of the third FET-enhanced N-MOS (V3), and the other end of the third diode (D3) is connected with the drain of the third FET-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 transistor enhanced N-MOS (V6), a fifth diode (D4), a second inductor (L2) and a sixth diode (D5), the source of the fifth field-effect transistor 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), the drain of the fifth field-effect transistor enhanced N-MOS (V6) is connected with the second module, one end of the sixth diode (D5) is connected with the source of the fifth field-effect transistor enhanced N-MOS (V6), and the other end of the sixth diode (D5) is connected with the drain of the fifth field-effect transistor enhanced N-MOS (V6).
3. A spacecraft power supply controller is characterized by comprising the power supply device as claimed in any one of claims 1-2, wherein the power supply device is adopted to design a solar cell array power regulator according to power requirements, the solar cell array power regulator is used for power regulation of a solar cell array in an illumination period and storage battery charging, the MPPT function before orbit transfer is realized, and the shunt regulation function is realized after the orbit transfer.
4. A spacecraft power supply controller according to claim 3, wherein a synchronous Buck and power supply means are employed to regulate the output power of the solar array during the illumination period and to charge the battery, a single converter is used to achieve MPPT + synchronous Buck before track transfer and shunt regulation after track transfer, Buck representing a Buck circuit.
5. A spacecraft power supply controller according to claim 4, wherein electric propulsion works before orbit transfer, the spacecraft power supply controller defaults to BUCK working in the shunt regulation part, when electric propulsion is effective, MPPT control keeps the solar panel working at the maximum power point, and the whole power supply controller works at the maximum power point, so that effective energy supply is ensured.
6. A spacecraft power supply controller according to claim 3, wherein the FSBB is adapted to enable bi-directional flow of input and output power, with the power supply means.
7. A spacecraft power supply controller according to claim 6, wherein the FSBB comprises a first switch tube (Q1), a second switch tube (Q2), a third switch tube (Q3), a fourth switch tube (Q4), an inductor (L), a first capacitor and a second capacitor, the source of the first switch tube (Q1) is connected with the drain of the second switch tube (Q2), the drain of the first switch tube (Q1) is connected with one end of the first capacitor, and the source of the second switch tube (Q2) is connected with the other end of the first capacitor; the source electrode of the third switch tube (Q3) is connected with the drain electrode of the fourth switch tube (Q4), the drain electrode of the third switch tube (Q3) is connected with one end of the second capacitor, the source electrode of the fourth switch tube (Q4) is connected with the other end of the second capacitor and the source electrode of the second switch tube (Q2), one end of the inductor (L) is connected between the first switch tube (Q1) and the second switch tube (Q2), and the other end of the inductor (L) is connected between the third switch tube (Q3) and the fourth switch tube (Q4).
8. A spacecraft power supply controller according to claim 7, wherein when Vin > Vo, BUCK mode is operated, when the third switching tube (Q3) is long-passed, the first switching tube (Q1) and the second switching tube (Q2) perform voltage reduction conversion function; when Vin is approximately equal to Vo, the Buck-Boost mode is adopted, 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) all work to complete a voltage conversion function; when Vin < Vo, the converter works in a Boost mode, the first switching tube (Q1) is in a long-pass state, and the third switching tube (Q3) and the fourth switching tube (Q4) complete a Boost conversion function.
9. A control method of a spacecraft power controller based on any one of claims 3-8, wherein before the spacecraft runs on a transfer orbit, a power supply device works in a DC/DC power conversion state, when the bus power is smaller than the sum of sailboard energy and battery charging current, the power supply device is controlled by an MEA (membrane electrode assembly) to stabilize the bus voltage, and at the moment, a battery is charged according to a set current gear; when the load of the bus is gradually increased until the power of the bus is greater than the sum of the energy of the sailboard and the charging current of the battery, the power supply device enters an MPPT mode, the maximum capacity of the sailboard is used as the load to supply energy, and the charging current of the battery 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 a transfer orbit, the power supply device realizes the switching between the DC/DC converter and the S3R circuit under the control of a bus conversion instruction, and the control logic of the circuit is as follows: when the power of the bus is less than the sum of the energy of the sailboard and the charging current of the battery, the power supply device is controlled by the MEA to work in a sequential shunt regulation mode, at the moment, the MPS3R module realizes the stability of the bus, and the battery is charged according to the set current gear; when the load of the bus is gradually increased until the power of the bus is greater than the sum of the energy of the sailboard and the charging current of the battery, the power supply device enters a full power supply mode, and the charging current of the battery 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.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114265468A (en) * | 2021-12-22 | 2022-04-01 | 深圳航天东方红卫星有限公司 | Solar cell array power regulation and fusion system |
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| Publication number | Priority date | Publication date | Assignee | Title |
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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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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114265468A (en) * | 2021-12-22 | 2022-04-01 | 深圳航天东方红卫星有限公司 | Solar cell array power regulation and fusion system |
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