CN111181238B - DET power supply system of satellite - Google Patents
DET power supply system of satellite Download PDFInfo
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- CN111181238B CN111181238B CN202010017148.1A CN202010017148A CN111181238B CN 111181238 B CN111181238 B CN 111181238B CN 202010017148 A CN202010017148 A CN 202010017148A CN 111181238 B CN111181238 B CN 111181238B
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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
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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
- 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
- H02J7/0029—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with safety or protection devices or circuits
- H02J7/0031—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with safety or protection devices or circuits using battery or load disconnect circuits
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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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- Sustainable Energy (AREA)
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- Electromagnetism (AREA)
- General Physics & Mathematics (AREA)
- Radar, Positioning & Navigation (AREA)
- Automation & Control Theory (AREA)
- Charge And Discharge Circuits For Batteries Or The Like (AREA)
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Abstract
The embodiment of the application provides a DET power supply system of a satellite, which is used for improving the output power of a solar cell array of the DET power supply system at the initial stage of the satellite. The power supply system comprises a solar cell array, a power supply control and power distribution unit and a storage battery pack, wherein the power supply control and power distribution unit comprises an S3R shunt regulator, an MEA (membrane electrode assembly) and a reference voltage module; the solar cell array is used for converting the acquired solar energy into electric energy; the S3R shunt regulator is used for performing shunt control according to the differential signal; the MEA is used for amplifying and integrating the difference between the reference voltage and the bus voltage controlled by the S3R shunt regulator to obtain a differential signal and outputting the differential signal to the S3R shunt controller; the reference voltage module is used for generating a reference voltage; the storage battery pack is connected with the bus and used for charging and discharging according to shunt control; the reference voltage module is specifically configured to generate different target reference voltages, and the S3R shunt controller is specifically configured to obtain different target bus voltages according to the target differential signal control.
Description
Technical Field
The application relates to the field of satellites, in particular to a DET power supply system of a satellite.
Background
The small satellite generally has a high integration level, and correspondingly, a power supply system of the small satellite also has the high integration level.
An existing power supply system of a small satellite can adopt a power supply system of a Direct Energy Transfer (DET) technology, which is called a DET power supply system for short, and the DET power supply system has the characteristic of high transmission efficiency.
In the existing DET power supply system, due to the characteristic that a power point cannot be adjusted, in order to ensure the output power of the power supply system at the end of the service life of a small satellite, the calculated voltage of the maximum power point at the end of the solar cell array is usually fixedly set, so that the maximum output power which can be output by the solar cell array at the end and the highest solar energy utilization rate are ensured, and meanwhile, the output power of the solar cell array at the initial stage and the solar energy utilization rate are lower.
Disclosure of Invention
The embodiment of the application provides a DET power supply system of a satellite, which is used for improving the output power of a solar cell array of the DET power supply system at the initial stage of the satellite.
The embodiment of the application provides a DET power supply system of a satellite, which comprises a solar cell array, a power supply control and power distribution unit and a storage battery pack, wherein the power supply control and power distribution unit comprises an S3R shunt regulator, a Main Error Amplifier (MEA) and a reference voltage module;
the solar cell array is used for converting the acquired solar energy into electric energy;
the S3R shunt regulator is used for performing three-domain control according to the differential signal;
the MEA is used for amplifying and integrating the difference between the reference voltage and the bus voltage controlled by the S3R shunt regulator to obtain a differential signal and outputting the differential signal to the S3R shunt controller, and the bus voltage is used for providing power for the load module;
the reference voltage module is used for generating a reference voltage;
the storage battery pack is connected with a bus for transmitting bus voltage and is used for charging and discharging according to shunt control;
in the working process, the reference voltage module is specifically configured to generate different target reference voltages, the MEA is specifically configured to generate a target differential signal according to the target reference voltage, and the S3R shunt controller is specifically configured to output different target bus voltages according to the target differential signal.
In the first exemplary embodiment of the present application, the reference voltage module is specifically configured to generate a target reference voltage corresponding to the maximum power point of the solar cell array, and the S3R controller is specifically configured to output a target bus voltage corresponding to the maximum power point of the solar cell array according to the target differential signal.
In a second exemplary embodiment of the present application, the reference voltage module includes a reference voltage generation module and a multi-way switch, the reference voltage generation module includes different voltage-dividing resistance lines connected to a voltage source, the different voltage-dividing resistance lines lead out voltage output interfaces for outputting different voltage levels, and the multi-way switch is configured to gate a target voltage interface corresponding to a target reference voltage from among the plurality of voltage output interfaces and output the target reference voltage to the MEA.
In a third exemplary embodiment of the present application, the reference voltage module includes a D/a converter for obtaining a target reference voltage from a voltage source through D/a conversion and outputting the target reference voltage to the MEA.
In a fourth exemplary embodiment of the present application, the power control and distribution unit is disposed between the storage battery pack and the bus bar, and further includes a charge protection module for preventing the storage battery pack from being overcharged and a discharge protection module for preventing the storage battery pack from being overdischarged.
In combination with the fourth exemplary embodiment of the present application, in a fifth exemplary embodiment of the present application, the charging protection module includes a termination voltage setting module, a comparing module, a Pulse Width Modulation (PWM) module, a driving circuit, a power switching tube, and a power diode;
the termination voltage setting module is used for setting the termination voltage of the storage battery pack;
the comparison module consists of a hysteresis comparator and is used for comparing the voltage obtained by sampling the storage battery pack with the termination voltage set by the termination voltage setting module and then outputting a corresponding level;
the PWM module is used for converting the level output by the comparison circuit into a PWM signal;
the driving circuit is used for amplifying the PWM signal into a driving signal capable of driving the power switch tube to be switched on and switched off;
the power switch tube is used for controlling the on-off of a charging loop according to the driving signal, and the charging loop is positioned between the storage battery pack and the bus;
the power diode is used for preventing the storage battery from being over-discharged due to the fact that the storage battery continues to discharge through the charging loop when the voltage of the storage battery is lower than the low-voltage threshold value.
In combination with the fourth exemplary embodiment of the present application, in a sixth exemplary embodiment of the present application, the discharge protection module includes a hysteresis comparator, a hardware protection enabling module, a software control module, a driving circuit, and a power switch tube;
the in-phase end of the hysteresis comparator is the over-discharge protection voltage value of the storage battery pack, and the reverse-phase end is the voltage sampling value of the storage battery pack;
the hardware protection enabling module is used for controlling the hardware protection circuit, and when the enabling is forbidden, the output end of the hysteresis comparator is disconnected with the control end of the power switch tube through the relay;
the driving circuit is used for amplifying a signal output by the output end of the hysteresis comparator into a driving signal capable of driving the power switch tube to be switched on and off;
the power switch tube is used for controlling the on-off of a discharge loop according to the driving signal, and the discharge loop is positioned between the storage battery pack and the bus;
the software control module is used for controlling the on-off of the power switch tube according to the control instruction;
when the storage battery pack normally works, the voltage of the inverting terminal is higher than the reference voltage;
when the storage battery pack has an over-discharge fault, the software control module controls the turn-off of the discharge path, and when the software control module fails to control and the voltage sampling value of the storage battery pack is lower than the over-discharge protection voltage threshold, the hardware protection module overturns the level of the hysteresis comparator and outputs low level to turn off the power switch tube so as to complete the over-discharge protection of the storage battery pack.
In a seventh exemplary embodiment of the present application, the power control and distribution unit further includes a secondary power conversion module between the bus and the load module, and the secondary power conversion module is configured to convert a voltage level of a bus voltage into a voltage level of an operating voltage of the load module.
With reference to the seventh exemplary embodiment of the present application, in an eighth exemplary embodiment of the present application, the secondary power conversion module includes a DC/DC chip, and the DC/DC chip is configured to select a target voltage level from a plurality of preset voltage levels for voltage level conversion according to a received control command.
In combination with the seventh exemplary embodiment of the present application, in the ninth exemplary embodiment of the present application, the secondary power conversion module includes a DC/DC conversion circuit for steplessly adjusting the voltage level according to the control parameter.
According to the technical scheme, the embodiment of the application has the following advantages:
in the working process of the DET power supply system of the satellite, because the reference voltage module in the embodiment of the application is configured, different reference voltages can be provided for the MEA, so that the MEA can generate different differential signals, in this case, the S3R shunt controller can control to obtain different bus voltages according to different differential signals in the process of shunt control (or S3R three-domain control), correspondingly, the solar cell array side can correspond to different bus voltages to realize different output powers, and thus in the DET power supply system, the effect of adjusting the output power of the solar cell array is realized, the defect that the output power of the solar cell array of the existing DET power supply system is lower in the initial stage of the satellite can be overcome to a certain extent, and the output power of the solar cell array of the initial stage of the satellite can be improved according to actual requirements and actual conditions.
Drawings
Fig. 1 is a schematic circuit diagram of a DET power supply system of a conventional satellite;
fig. 2 is a schematic circuit diagram of a DET power supply system of a satellite according to an embodiment of the present invention;
fig. 3 is a schematic circuit diagram of a charging protection module according to an embodiment of the present disclosure;
fig. 4 is a schematic circuit diagram of a discharge protection module according to an embodiment of the present application;
FIG. 5 is a schematic flow chart illustrating on-track charging management of a battery pack according to an embodiment of the present disclosure;
fig. 6 is a schematic circuit structure diagram of a TPS54560 chip according to an embodiment of the present application.
Detailed Description
The embodiment of the application provides a DET power supply system of a satellite, which is used for improving the output power of a solar cell array of the DET power supply system at the initial stage of the satellite.
The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are only a part of the embodiments of the present application, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
Before describing the DET power supply system for a satellite in detail, embodiments of the present application will be described briefly with reference to the related background.
Minisatellites, such as commercial minisatellites, typically have the following characteristics: firstly, the development period is short, usually not more than two years, and the manufacturing process of the satellite is gradually transited from a ' craftsman ' to a ' production line type, while the development period of a large satellite is generally 7-8 years; the launching mode is flexible, the satellite can be launched independently by a small carrier rocket, can be launched along with other satellites in a 'lift-up' mode, can launch a plurality of small satellites by one rocket, and even can be transported to a space station and released to the space by a mechanical arm; thirdly, the cost is low, generally, one small satellite has the cost of about 3000 million RMB including the emission price, not only the price is low, but also the risk is small, in addition, the service life of the small satellite is more than 10 years generally, and the capital barrier of the satellite industry is greatly reduced; fourthly, the survival ability is strong, the small satellite group is used for replacing a single large satellite, so that the ten-in-one effect can be realized, the small satellite group and the large satellite are mutually used as backup, and the whole system can be damaged and persist in combat; fifthly, the application range is wide, the method can be applied to various aspects such as communication, remote sensing, scientific research, military and the like, and is suitable for carrying out new technology tests; and sixthly, the satellite constellation is strong in function and easy to form on different orbits, so that the function which cannot be realized by a single satellite is realized.
Meanwhile, the power supply system of the small satellite also has the characteristics of high integration level, strong universality, low development cost, short construction period and the like.
In the power supply system of the existing small satellite, two main types are adopted according to the power regulation mode: a Power supply system adopting the DET technology, and a Power supply system adopting a Maximum Power Point Tracking (MPPT) control technology.
The DET power supply system has high transmission efficiency, a simple circuit structure and easy realization, the working point of the solar cell array changes along with the load, the initial energy utilization rate is low, and the final energy utilization rate is high; the MPPT power supply system can provide power according to the requirement of a load, the solar cell array can always output the maximum power, the light energy conversion efficiency is high, the circuit structure is complex, and the voltage conversion and tracking algorithm realization circuit needs to consume certain power, so that the transmission efficiency is low.
The MPPT power supply system has the advantages that the size and the weight are increased due to the existence of the DC/DC converter in the system topology, the cost is increased, meanwhile, the heat consumption and the power consumption of the power supply system are increased, particularly in the illumination period, the heat consumption is obviously higher than that of the traditional DET power supply system, great difficulty is brought to the heat control of the whole satellite, and therefore the MPPT power supply system is not adopted in the small satellite, particularly the commercial small satellite, and the DET power supply system is generally adopted.
In the conventional DET power supply system, as shown in fig. 1, a schematic structural diagram of the conventional satellite DET power supply system is that a reference voltage to an MEA is constant, so that a bus voltage is also constant, and there is a characteristic that a power point cannot be adjusted.
Based on the defects of the prior art, the embodiment of the application provides a new DET power supply system for a satellite, which can overcome the defects of the prior art to a certain extent.
In the following, a DET power supply system for a satellite according to an embodiment of the present application will be described based on the related background.
The satellite DET power supply system provided by the embodiment of the application comprises a solar cell array, a power supply control and power distribution unit and a storage battery pack, wherein the power supply control and power distribution unit comprises an S3R shunt regulator, a main error amplifier MEA (membrane electrode assembly) and a reference voltage module;
the Power Control and distribution Unit further includes a remote measurement and Control module, a Power Control Unit (PCU) module, a primary Power distribution module, a secondary Power distribution module, and an initiating explosive device module. The telemetering and remote control module is responsible for collecting analog quantity and state quantity, arranging the analog quantity and the state quantity into bus telemetering and uploading, and responsible for decoding external bus instructions and transmitting the external bus instructions to each internal module; the PCU module is responsible for adjusting the power of the satellite illuminator, charging the storage battery pack, adjusting the power of the earth shadow period and the like; the primary power distribution module and the secondary power distribution module are responsible for primary power supply and secondary power supply of the whole satellite and have a fault isolation function; and the initiating explosive device module is responsible for initiating explosive device detonation control of the whole star. For convenience of description, the drawings shown in the embodiments of the present application only show the S3R shunt regulator, the MEA, the reference voltage module, the charge protection module, and the discharge protection module, which are related to the embodiments of the present application, and the power control and distribution module, which is not shown in the drawings, should further include the above-mentioned components such as the telemetry remote control module, the PCU module, the primary power distribution module, the secondary power distribution module, or the initiating explosive device module.
The solar cell array is used for converting the acquired solar energy into electric energy;
the S3R shunt regulator is used for performing shunt control according to the differential signal;
the MEA is used for amplifying and integrating the difference between the reference voltage and the bus voltage controlled by the S3R shunt regulator to obtain a differential signal and outputting the differential signal to the S3R shunt controller, and the bus voltage is used for providing power for the load module;
the reference voltage module is used for generating a reference voltage;
the storage battery pack is connected with a bus for transmitting bus voltage and is used for charging and discharging according to shunt control, namely, the storage battery pack is used for storing energy in an illumination period and supplying energy to a load in a ground shadow period;
in the working process, the reference voltage module is specifically configured to generate different target reference voltages, the MEA is specifically configured to generate a target differential signal according to the target reference voltage, and the S3R shunt controller is specifically configured to control to obtain different target bus voltages according to the target differential signal.
In the technical solution of the above embodiment, it can be seen that, during the operation of the DET power supply system of the satellite, with the reference voltage module in the embodiment of the present application, different reference voltages can be supplied to the MEA, so that the MEA can generate different differential signals, in this case, the S3R shunt controller can control the bus voltage to be different according to different differential signals during the shunt control (or S3R three-domain control), correspondingly, the solar cell array side can correspond to different bus voltages to realize different output powers, therefore, in the DET power supply system, the effect of regulating the output power of the solar cell array is realized, can overcome the defect that the output power of the solar cell array of the prior DET power supply system is lower at the initial stage of the satellite to a certain extent, and the output power of the solar cell array at the initial stage of the satellite can be adjusted and improved according to actual requirements and actual conditions.
Specifically, under the conditions that the illumination condition changes slowly and the illumination time is relatively stable, the reference voltage module can fix the reference voltage within a period of time, and the reference voltage is reset once in a period of time, so that the solar cell array always works at a higher power point, the purpose of flexibly improving the output efficiency of the solar cell array at the initial stage of the satellite is achieved, and the flexible and changeable use requirements of the power supply system of the commercial small satellite on load can be met.
In addition, it should be noted that, in the DET power supply system of the existing satellite, the bus voltage is fixed, and an access system of the storage Battery pack needs to be provided with an independent charging Regulator (BCR) and a discharging Regulator (BDR) to assist in supplying power to the load module, which greatly increases the volume and mass, increases the circuit design complexity, increases the types and number of components and parts, and increases the development cost.
In the DET power supply system of the satellite provided by the embodiment of the application, the bus voltage can be adjusted, and therefore, an independent charging and discharging regulator is not needed to be arranged, the storage battery pack can be directly connected to the bus for transmitting the bus voltage, the cost is saved, the energy can be fully utilized, and the charging and discharging efficiency is high.
The above-described embodiments will now be described in further detail.
As an exemplary embodiment, the reference voltage module is specifically configured to generate a target reference voltage corresponding to the maximum power point of the solar cell array, and the S3R controller is specifically configured to output a target bus voltage corresponding to the maximum power point of the solar cell array according to the target differential signal.
It can be understood that the reference voltage generated by the reference voltage module can continuously adjust and regulate the power point, so that the solar cell array always keeps the highest power point under the current illumination condition, keeps the highest output power and achieves the purpose of maximum power point tracking.
In another exemplary embodiment, as shown in fig. 2, in a schematic structural diagram of a DET power supply system for a satellite according to an embodiment of the present invention, the reference voltage module may include a reference voltage generating module and a multi-way switch, the reference voltage generating module may include voltage output interfaces for outputting different voltage levels from a voltage source through different voltage dividing resistance lines, the different voltage dividing resistance lines may lead out voltage output interfaces for outputting different reference voltages according to the voltage output interfaces, and the multi-way switch may gate a target interface corresponding to a target reference voltage from among the multiple voltage output interfaces according to a control instruction and output the target reference voltage to the MEA, thereby achieving an objective of adjusting the reference voltage.
In practical applications, the voltage source may specifically be a bus voltage on a bus, or may also be a voltage provided or extracted by other devices.
It can be understood that, if the voltage source is a bus voltage, it is obviously further convenient to route and configure the DET power supply system, and no additional equipment is required to provide a voltage source for generating the reference voltage, so that the design cost and hardware cost of the DET voltage source can be further saved.
Meanwhile, in actual demand, if the adjustment gear of the reference voltage is required to be many, the D/a converter may be used instead of the voltage dividing resistor line to convert the reference voltage to obtain the required reference voltage, for example, the 8-bit D/a converter may be used to divide the reference voltage by 256 steps at most, thereby achieving 256-step adjustment of the bus voltage and achieving more detailed voltage conversion.
Of course, in practical applications, the two can be configured at the same time and used alternatively according to actual requirements.
In still another exemplary embodiment, in the case that the storage battery pack is directly connected to the bus bar, without providing a special BCR and BDR circuit, the power control and distribution unit may provide a charging protection module for preventing the storage battery pack from being overcharged and a discharging protection module for preventing the storage battery pack from being overdischarged between the storage battery pack and the bus bar, so as to realize on-rail efficient management of the storage battery pack.
In yet another exemplary embodiment, as a schematic circuit structure diagram of a charging protection module according to an embodiment of the present application shown in fig. 3, the charging protection module may include an end voltage setting module, a comparing module, a PWM module, a driving circuit, a power switch tube, and a power diode;
the termination voltage setting module is used for setting the termination voltage of the storage battery pack;
the comparison module consists of a hysteresis comparator and is used for comparing the voltage obtained by sampling the storage battery pack with the termination voltage set by the termination voltage setting module and then outputting a corresponding level;
the PWM module is used for converting the level output by the comparison circuit into a PWM signal;
the driving circuit is used for amplifying the PWM signal into a driving signal capable of driving the power switch tube to be switched on and switched off;
the power switch tube is used for controlling the on-off of a charging loop according to the driving signal, and the charging loop is positioned between the storage battery pack and the bus;
the power diode is used for preventing the storage battery pack from being discharged continuously through the charging loop when the voltage of the storage battery pack is lower than a low-voltage threshold value, so that the storage battery pack is over-discharged, and the service life of the storage battery pack is reduced.
In yet another exemplary embodiment, as shown in fig. 4, a circuit structure diagram of a discharge protection module according to an embodiment of the present application is provided, where the discharge protection module includes a hysteresis comparator, a hardware protection enabling module, a software control module, a driving circuit, and a power switch;
the in-phase end of the hysteresis comparator is the over-discharge protection voltage value of the storage battery pack, and the reverse-phase end is the voltage sampling value of the storage battery pack;
the hardware protection enabling module is used for controlling the hardware protection circuit, and when the enabling is forbidden, the output end of the hysteresis comparator is disconnected with the control end of the power switch tube through the relay;
the driving circuit is used for amplifying a signal output by the output end of the hysteresis comparator into a driving signal capable of driving the power switch tube to be switched on and off;
the power switch tube is used for controlling the on-off of a discharge loop according to the driving signal, and the discharge loop is positioned between the storage battery pack and the bus;
the software control module is used for controlling the on-off of the power switch tube according to the control instruction;
when the storage battery pack normally works, the voltage of the inverting terminal is higher than the reference voltage;
when the storage battery pack has an over-discharge fault, the software control module controls the turn-off of the discharge path, and when the software control module fails to control and the voltage sampling value of the storage battery pack is lower than the over-discharge protection voltage threshold, the hardware protection module overturns the level of the hysteresis comparator and outputs low level to turn off the power switch tube so as to complete the over-discharge protection of the storage battery pack.
When the satellite is in a long illumination season, the storage battery pack does not need to discharge, and the charging and discharging working condition of the storage battery pack is set to be a shelving management mode. The charging stopping voltage is set to be a corresponding voltage value when the capacity of the battery is 80%, and a discharging switch in the discharging control protection loop is disconnected by the software control module to open an electric switch, so that a discharging path is ensured to be disconnected.
When the satellite operates in orbit, the charging termination voltage of the storage battery pack can be dynamically adjusted through a control command from the ground. When the satellite is in a full-light area, the storage battery pack cannot discharge, when the solar battery array power is rich, the storage battery pack is charged by small trickle current all the time, and the service life and the capacity of the storage battery pack are influenced badly if the storage battery pack keeps a full-charge state for a long time. Therefore, the storage battery pack in the full-exposure period is necessary to be laid down and managed, the charging termination voltage of the storage battery pack can be reduced to enable the storage battery pack to correspond to about 80% of the battery capacity, the harm of floating charging to the storage battery pack is reduced, and the purpose of prolonging the service life of the storage battery pack is achieved.
Referring to fig. 5, which is a schematic flow diagram of on-orbit charging management of a storage battery pack according to an embodiment of the present disclosure, as shown in fig. 5, it is first determined whether a current satellite is in a long illumination season, a shelving management mode is switched, if the current satellite is not in the long illumination season, the current satellite is in a normal operating mode, a charging termination voltage is set according to a normal voltage of the storage battery pack, and after the storage battery pack is charged to a threshold voltage, a power switch tube is determined and cut off, so that an effect of preventing overcharge of the storage battery pack is achieved. And in the whole process, comparing the acquired voltage of the storage battery with a set lower limit of charging voltage, and if the voltage of the storage battery is lower than the lower limit voltage, opening a power switch tube of a charging path.
In another exemplary embodiment, the DET power supply system for a satellite provided in the embodiments of the present application may further include a secondary power distribution circuit, i.e., a secondary power conversion module, for performing voltage conversion on the load module side. The power control and distribution unit is arranged between the bus and the load module, and the power control and distribution unit further comprises a secondary electric energy conversion module, and the secondary electric energy conversion module is used for converting the voltage level of the bus voltage into the voltage level of the working voltage of the load module.
In another exemplary embodiment, the secondary power conversion module may be a DC/DC chip, and the DC/DC chip is configured to select a target voltage level from a plurality of preset voltage levels for voltage level conversion according to a received control instruction, so that the general design and mass production of the DET power supply system can be satisfied, and even if the rated voltage of a single load is adjusted, the power supply voltage can be general as long as the power supply voltage is within a range of gears.
In another exemplary embodiment, the secondary power conversion module may also be a DC/DC conversion circuit, and the DC/DC conversion circuit is configured to adjust the voltage level steplessly according to the control parameter, so that the distribution output of the DET power supply system can meet the usage requirement of the load module as long as the load supply voltage is within a reasonable range.
Of course, in practical applications, the two can be configured at the same time and used alternatively according to actual requirements.
For example, if the bus voltage is 28V class or 42V class, and the power distribution output is +12V, +5V, +5.5V, etc., the DC/DC chip may be implemented by a non-isolated step-down chip integrated with a PMOS transistor, for example, a TPS54560 chip, referring to a schematic circuit structure diagram of the TPS54560 chip in the embodiment of the present application shown in fig. 6, an input voltage range of the TPS54560 chip is 4.5V to 60V, a maximum output current 5A has a conversion efficiency of about 90%, and an output voltage thereof may be output with different voltage values by adjusting a voltage dividing resistor Rfbb of an FB pin. The multi-path distribution circuit is connected in parallel on the bus, so that the output of the multi-path distribution port of the power supply system can be realized, all the distribution circuits are isolated from each other, and the normal work of other distribution channels is not influenced even if one of the distribution circuits fails. The commercial satellite networking needs dozens or even hundreds of small satellites, and according to the factors such as service types and on-orbit functions, the single machines loaded on the satellite are not completely consistent, and the design idea can ensure that the DET power supply system can be continuously used under the condition that the supply voltage changes due to the replacement of single machine products, redesign is not needed, and the universality is very strong.
It can be understood that, in the embodiment of the present application, the control command of the multi-way switch, the control command of the D/a converter, the control command of the software module, the magnitude of the reference voltage, the control parameter of the DC/DC conversion circuit, and other information may be from a satellite management center on the ground, and the satellite is equipped with a corresponding controller for communicating with the ground and receiving related information, or the controller of the power supply control and power distribution unit or the PCU module in the power supply control and power distribution unit implements the data processing related to the above according to the stored program and information.
To sum up, the DET power supply system for a satellite provided in the embodiment of the present application is simple and effective for a management strategy and a realization circuit of a storage battery through adjustment and setting of a reference voltage, and can realize on-orbit management of the storage battery by using a relatively simple overcharge/overdischarge prevention protection circuit, and can realize single-path multiple voltage adjustability by adjusting the resistance value of the voltage dividing resistor of the FB pin of the DC/DC chip, and even if the power supply voltage changes along with a single machine or an effective load of a corresponding power distribution circuit, different voltage dividing resistors can be selected through the gating switch to output corresponding required voltages. The power supply system has the advantages of high energy utilization rate, low cost, relatively low design difficulty, short development period, strong universality and the like, and meets the use requirements and characteristics of small satellites, particularly commercial small satellites.
The above embodiments are only used to illustrate the technical solutions of the present application, and not to limit the same; although the present application has been described in detail with reference to the foregoing embodiments, it should be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions in the embodiments of the present application.
Claims (1)
1. The DET power supply system of a satellite is characterized by comprising a solar cell array, a power supply control and distribution unit and a storage battery pack, wherein the power supply control and distribution unit comprises an S3R shunt regulator, a main error amplifier MEA and a reference voltage module;
the solar cell array is used for converting the acquired solar energy into electric energy;
the S3R shunt regulator is used for performing shunt control according to the differential signal;
the MEA is used for amplifying and integrating the difference value between the reference voltage and the bus voltage controlled by the S3R shunt regulator to obtain the differential signal and outputting the differential signal to the S3R shunt controller, and the bus voltage is used for providing power supply for the load module;
the reference voltage module is used for generating the reference voltage;
the storage battery pack is connected with a bus for transmitting the bus voltage and is used for charging and discharging according to the shunt control;
in the working process, the reference voltage module is specifically configured to generate a target reference voltage corresponding to the maximum power point of the solar cell array, the MEA is specifically configured to generate a target differential signal according to the target reference voltage, and the S3R shunt controller is specifically configured to output a target bus voltage corresponding to the maximum power point of the solar cell array according to the target differential signal;
the reference voltage module comprises a reference voltage generating module and a multi-way switch, the reference voltage generating module comprises different voltage dividing resistance lines connected with a voltage source, voltage output interfaces used for outputting different voltage levels are led out from the different voltage dividing resistance lines, and the multi-way switch is used for gating a target voltage interface corresponding to the target reference voltage from a plurality of voltage output interfaces and outputting the target reference voltage to the MEA;
the DET power supply system, the reference voltage module comprises a D/A converter, and the D/A converter is used for obtaining the target reference voltage from a voltage source through D/A conversion and outputting the target reference voltage to the MEA;
the power control and distribution unit is arranged between the storage battery pack and the bus, and also comprises a charge protection module and a discharge protection module, wherein the charge protection module is used for preventing the storage battery pack from being overcharged, and the discharge protection module is used for preventing the storage battery pack from being overdischarged;
the charging protection module comprises a termination voltage setting module, a comparison module, a PWM module, a driving circuit, a power switch tube and a power diode;
the termination voltage setting module is used for setting the termination voltage of the storage battery pack;
the comparison module is composed of a hysteresis comparator and is used for comparing the voltage sampled by the storage battery pack with the termination voltage set by the termination voltage setting module and outputting a corresponding level;
the PWM module is used for converting the level output by the comparison circuit into a PWM signal;
the driving circuit is used for amplifying the PWM signal into a driving signal capable of driving the power switching tube to be switched on and switched off;
the power switch tube is used for controlling the on-off of a charging loop according to the driving signal, and the charging loop is positioned between the storage battery pack and the bus;
the power diode is used for preventing the storage battery pack from being over-discharged due to the fact that the storage battery pack is continuously discharged through the charging loop when the voltage of the storage battery pack is lower than a low-voltage threshold;
the discharge protection module comprises a hysteresis comparator, a hardware protection enabling module, a software control module, a driving circuit and a power switch tube;
the in-phase end of the hysteresis comparator is an over-discharge protection voltage value of the storage battery pack, and the reverse-phase end of the hysteresis comparator is a voltage sampling value of the storage battery pack;
the hardware protection enabling module is used for controlling a hardware protection circuit, and when the enabling is forbidden, the output end of the hysteresis comparator is disconnected with the control end of the power switch tube through a relay;
the driving circuit is used for amplifying a signal output by the output end of the hysteresis comparator into a driving signal capable of driving the power switch tube to be switched on and switched off;
the power switch tube is used for controlling the on-off of a discharge loop according to the driving signal, and the discharge loop is positioned between the storage battery pack and the bus;
the software control module is used for controlling the on-off of the power switch tube according to a control instruction;
when the storage battery pack works normally, the voltage of the inverting terminal is higher than the reference voltage; when the storage battery pack has an over-discharge fault, the software control module controls the turn-off of the discharge loop, and when the software control module fails to control and the voltage sampling value of the storage battery pack is lower than an over-discharge protection voltage threshold, the hardware protection enabling module overturns the level of the hysteresis comparator and outputs a low level so as to turn off the power switch tube and complete the over-discharge protection of the storage battery pack;
the power supply control and distribution unit is arranged between the bus and the load module and also comprises a secondary electric energy conversion module, and the secondary electric energy conversion module is used for converting the voltage grade of the bus voltage into the voltage grade of the working voltage of the load module;
the secondary electric energy conversion module comprises a DC/DC chip, and the DC/DC chip is used for selecting a target voltage grade from a plurality of preset voltage grades to convert the voltage grade according to a received control instruction;
the secondary electric energy conversion module comprises a DC/DC conversion circuit, and the DC/DC conversion circuit is used for stepless regulation of voltage grade according to control parameters;
the storage battery pack does not need to be discharged in long illumination seasons, the charging and discharging working condition of the storage battery pack is set to be a shelving management mode, the charging termination voltage of the storage battery pack is set to be a corresponding voltage value when the capacity of the battery is 80%, and a discharging switch in a discharging control protection loop of the storage battery pack is switched off and switched on by a software control module.
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| CN112462290B (en) * | 2020-09-30 | 2023-03-07 | 上海空间电源研究所 | Ground simulation comparison test system and method for power supply system |
| CN112362991A (en) * | 2020-11-05 | 2021-02-12 | 中国空间技术研究院 | Component aging test device monitoring system and method for aerospace |
| CN112636446B (en) * | 2020-12-29 | 2022-03-01 | 中国人民解放军国防科技大学 | Power supply system of quick response small satellite |
| CN112838660A (en) * | 2020-12-31 | 2021-05-25 | 上海移为通信技术股份有限公司 | Solar charging circuit, charging method, electronic device and storage medium |
| CN112910030B (en) * | 2021-01-18 | 2022-02-15 | 中国科学院微小卫星创新研究院 | On-orbit autonomous management system and method of satellite energy system |
| CN112865242B (en) * | 2021-01-27 | 2023-02-14 | 上海交通大学 | Multi-energy interconnection power supply energy control system and method for satellite power supply system |
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| CN113507100A (en) * | 2021-06-09 | 2021-10-15 | 上海空间电源研究所 | Bus overvoltage protection control system of spacecraft power supply system |
| CN113300450B (en) * | 2021-06-28 | 2023-06-20 | 上海空间电源研究所 | Satellite power supply controller |
| CN113791663B (en) * | 2021-07-19 | 2022-09-27 | 北京空间飞行器总体设计部 | High-power spacecraft power supply system based on solar cell array maximum power point tracking technology |
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| CN113761688A (en) * | 2021-09-10 | 2021-12-07 | 上海卫星工程研究所 | Method for batch production of small satellite cable networks |
| CN114024351B (en) * | 2021-11-09 | 2023-04-18 | 北京微纳星空科技有限公司 | Power supply system and power supply method used in satellite |
| CN114488888B (en) * | 2022-01-14 | 2024-01-30 | 上海卫星工程研究所 | spaceVPX architecture-based satellite-borne stand-alone dual-redundancy high-reliability power supply |
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