CN114784939A - Distributed low-orbit small satellite power supply system - Google Patents

Distributed low-orbit small satellite power supply system Download PDF

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Publication number
CN114784939A
CN114784939A CN202210366718.7A CN202210366718A CN114784939A CN 114784939 A CN114784939 A CN 114784939A CN 202210366718 A CN202210366718 A CN 202210366718A CN 114784939 A CN114784939 A CN 114784939A
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bus
power supply
voltage
solar cell
module
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常正勇
韩献堂
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Beijing Juntian Hangyu Technology Co ltd
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Beijing Juntian Hangyu Technology Co ltd
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    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
    • H02J7/34—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering
    • H02J7/35—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering with light sensitive cells
    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05F—SYSTEMS FOR REGULATING ELECTRIC OR MAGNETIC VARIABLES
    • G05F1/00—Automatic systems in which deviations of an electric quantity from one or more predetermined values are detected at the output of the system and fed back to a device within the system to restore the detected quantity to its predetermined value or values, i.e. retroactive systems
    • G05F1/66—Regulating electric power
    • G05F1/67—Regulating electric power to the maximum power available from a generator, e.g. from solar cell
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02H—EMERGENCY PROTECTIVE CIRCUIT ARRANGEMENTS
    • H02H7/00—Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions
    • H02H7/26—Sectionalised protection of cable or line systems, e.g. for disconnecting a section on which a short-circuit, earth fault, or arc discharge has occured
    • 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
    • H02J3/00—Circuit arrangements for ac mains or ac distribution networks
    • H02J3/38—Arrangements for parallely feeding a single network by two or more generators, converters or transformers
    • H02J3/381—Dispersed generators
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
    • H02J7/0068—Battery or charger load switching, e.g. concurrent charging and load supply
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J2300/00—Systems for supplying or distributing electric power characterised by decentralized, dispersed, or local generation
    • H02J2300/20—The dispersed energy generation being of renewable origin
    • H02J2300/22—The renewable source being solar energy
    • H02J2300/24—The renewable source being solar energy of photovoltaic origin

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  • Engineering & Computer Science (AREA)
  • Power Engineering (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Sustainable Energy (AREA)
  • Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • General Physics & Mathematics (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Automation & Control Theory (AREA)
  • Charge And Discharge Circuits For Batteries Or The Like (AREA)

Abstract

The invention discloses a distributed low-orbit small satellite power supply system, which has the advantages of simple structure, high specific power, flexible configuration and the like compared with the traditional S3R and S4R mode full-regulation framework, can realize full regulation of a bus and simultaneously utilize sunlight to generate electricity to the maximum extent, and increases the generating efficiency of the system; compared with the existing MPPT mode architecture, the charging and discharging module with the same hardware structure is arranged at the storage battery end, so that the bus full-regulation function is realized, and meanwhile, the distributed system architecture is provided, so that the reliability of the system is greatly enhanced; the energy storage battery adopts 21700 lithium ion battery, compared with 18650 battery adopted in the prior art, has the advantage of large specific energy, can lighten the weight of the storage battery under the same energy requirement, reduce the satellite launch cost; the distributed power system, the power generation unit and the energy storage battery pack are connected to the bus through the power electronic device, and all units are not influenced with each other, can be isolated in time if a fault occurs, cannot cause great influence on the system, and can work normally.

Description

Distributed low-orbit small satellite power supply system
Technical Field
The invention relates to the technical field of miniature power supply, in particular to a distributed low-orbit small satellite power supply system.
Background
Low Earth Orbit (LEO) satellites operate orbitally about 100km to 1000km from the earth's surface, much lower than conventional high earth orbit communication satellites, and have a strong speed response capability that allows frequent radio contact of the satellite with terrestrial base stations. LEO satellites are widely used for civil, scientific, and military purposes, such as ground observation, radar, optical, telecommunication, and exercise airplanes. With the rapid development of LEO satellites, the power requirement of LEO satellites gradually increases, but the LEO satellites are limited by the size of the satellites, and a solar cell array cannot be enlarged, so that the constraint relation is a prominent problem restricting the development of small satellites, and the defects of the architecture of the traditional satellite power supply system are revealed and will be more prominent.
A general medium and high orbit satellite power supply system adopts an S3R topology structure, as shown in fig. 2, the topology structure mainly includes three parts of a shunt, a charger and a discharger, a solar cell array and the shunt are connected in parallel and then output a bus, the charger is responsible for taking power from the bus to charge a storage battery, and the discharger is responsible for discharging and adjusting the storage battery to stabilize the bus voltage, and is a full-adjustment bus topology of a traditional three-domain adjusting mode. The bus voltage regulating circuit has the advantages that the bus is fully regulated, a stable and efficient bus voltage can be provided, and the bus voltage regulating circuit has the defects of relatively complex topology, relatively low energy-to-weight ratio and relatively less application in low-orbit satellites.
The low-orbit satellite is characterized by low orbit, short earth-surrounding period, large instantaneous power of satellite load, short orbit period, multiple light and shadow cycles, and the battery pack needs to be filled in a short time, so that the power supply system of the satellite also needs to be properly adjusted, and fig. 3 shows the topology of the common S4R power supply system of the low-orbit satellite. In the high orbit satellite, the illumination time is long, charging module (BCR) need be used less, usually the undercurrent charges can, S3R topology is comparatively economical, and the low orbit satellite illumination time is comparatively short, the battery needs frequent charging, BCR need use more, on the other hand, Shunt (SUN) need shunt unnecessary current in order to stabilize the bus voltage, consequently S4R topology utilizes the shunt directly to charge for the battery, can save BCR module, the energy utilization and the weight rate of system have been improved.
In order to further improve the energy utilization rate, a peak power tracking (MPPT) mode is adopted to decouple the solar array working point and the bus voltage, so that the solar cell array can work at the maximum power point under any load conversion and environmental change, the output power of the solar cell array is fully exerted, the instantaneous high-power requirement of the load of the LEO satellite is favorably met, the area of the solar array is reduced, and the development requirements of high power and light weight of a power supply system of the LEO satellite are met.
In most of the existing patents, a maximum power point tracking circuit is directly mounted on a bus, as shown in fig. 4, a relatively simple MPPT method is adopted to realize maximum power output of a solar cell array, and simultaneously, the voltage of a lithium ion battery sub-clamping bus is controlled, but no storage battery discharge regulation exists in the patent, the bus belongs to a half-regulation bus, and the power supply efficiency is relatively low.
Disclosure of Invention
The present invention provides a distributed low-earth-orbit small satellite power system to solve the problems of the prior art.
In order to achieve the purpose, the invention provides the following technical scheme:
a distributed low-orbit small satellite power supply system comprises a solar cell array, a photovoltaic adjusting unit, a storage battery pack, a charge and discharge adjusting module, a bus filtering module and an external load, wherein the photovoltaic adjusting unit and the charge and discharge adjusting module are provided with the same hardware circuit, and injection software algorithms of the photovoltaic adjusting unit and the charge and discharge adjusting module are different;
the solar cell array adopts a modular subarray design, and each subarray is an independent power supply unit;
the storage battery pack adopts 21700 standard electric core with higher specific energy to combine into 10 groups of battery packs;
a capacitor module in the bus filter module adopts a film capacitor with a self-healing function;
the solar cell array is electrically connected with the photovoltaic adjusting unit, the storage battery pack is electrically connected with the charge-discharge adjusting module, the photovoltaic adjusting unit and the charge-discharge adjusting module are both electrically connected with a system bus, and the system bus is electrically connected with a bus load and a bus capacitor to form a power supply system.
Preferably, the solar cell array adopts high-efficiency film type gallium arsenide solar cell monomers, each high-efficiency film type gallium arsenide solar cell monomer is combined into small assemblies with required voltage and current in a imbricated splicing mode, and the small assemblies form a sub-array through a series-parallel circuit;
the solar cell array comprises 10 solar cell sub-arrays, each sub-array is provided with one photovoltaic adjusting unit to form a power generation unit, and each power generation unit is independently connected to the system bus.
Preferably, the photovoltaic adjusting unit circuit unit comprises a DCDC boost circuit and a DSP control circuit;
the input end of the photovoltaic adjusting unit is a solar cell subarray, and the output end of the photovoltaic adjusting unit is a system bus;
the state of a DCDC circuit switching tube is regulated in a PWM mode so as to realize the maximum power tracking of the solar cell array and utilize the solar energy to the maximum extent;
and each DSP control circuit is respectively corresponding to one DCDC circuit to carry out closed-loop control.
Preferably, the DSP control circuit comprises a TMS320F2808 controller and a MOSFET driver chip, and the TMS320F2808 controller and the MOSFET driver chip inject an MPPT algorithm to adjust the duty cycle of the switching tube of the DCDC circuit, thereby adjusting the output voltage of the solar cell array and tracking the maximum power thereof;
the MPPT algorithm adopts a disturbance observation method and a genetic algorithm dual-mode control, when the change of the maximum power point is small, the maximum power point is tracked by a small step disturbance observation method, when the external change is not large, the difference of the maximum power points is not large, the former maximum power point is reserved, the next round of tracking is directly carried out, and when the external change is large, the tracking is carried out according to the disturbance method.
Preferably, the storage battery pack is formed by combining 21700 standard battery cores with higher specific energy in a mode of 2 parallel 12 series connection, the rated voltage of the battery pack is 42V, and the capacity of the battery pack is 8.4Ah, and each battery pack is provided with a charging and discharging adjusting module to form a power supply module access system bus.
Preferably, the charging and discharging regulating module comprises a DCDC circuit capable of increasing and decreasing voltage and a DSP control circuit;
one end of the charge and discharge adjusting module is connected with the storage battery pack, and the other end of the charge and discharge adjusting module is connected with a system circuit bus;
the control function is realized by injecting an algorithm into the charging and discharging regulation module, the state of the switching tube is regulated according to external requirements, when the main topology is in a voltage reduction mode, the charging device is used for charging the storage battery by taking power from the system bus, and when the main topology is in a voltage increase mode, the discharging regulator is used for discharging the system bus and regulating the voltage of the system bus;
the charge and discharge regulation module adopts a PI double closed-loop control method, and comprises two control parts: current inner loop PI control and voltage outer loop PI control;
current inner loop control: the current flowing through the inductor is the current with given amplitude and phase through the means of current negative feedback;
voltage outer loop control: negative feedback of voltage is introduced, so that the voltage on the direct current side is stabilized to be a given value, and the system bus voltage is adjusted.
Preferably, each solar cell sub-array in the solar cell array is connected to the system bus through the photovoltaic adjusting unit, each battery pack is connected to the system bus through the charging and discharging adjusting module, the two modules form a distributed power system framework, and each power supply unit is independent.
Preferably, the bus filtering module is connected between the positive electrode and the negative electrode of the bus, and filters the current in the system bus based on the internal capacitor, so as to shield the unnecessary alternating current component and smooth the direct current;
the film type capacitor adopts a polypropylene film as a medium, a layer of thin metal is evaporated on the surface of the polypropylene film as a conductive electrode, when an overhigh voltage is applied, the electric weakness of the polypropylene film is broken down, the resistance of a breakdown point is obviously reduced, the density of the flowing current is sharply increased, so that the metalized coating generates high heat, a metal conductor around the breakdown point is quickly evaporated and dissipated to form a blank area of the metal coating, the breakdown point automatically recovers insulation, and the reliability of a power supply system is improved.
Preferably, the load comprises two parts:
one is an on-satellite payload that can accommodate a dc 42V supply voltage;
the other is a satellite power distributor which mainly has the function of converting a 42V direct current bus into different output voltages so as to meet the requirements of other loads on the satellite;
meanwhile, the load can meet the energy balance of the whole satellite power supply system by adjusting the power requirement.
Compared with the prior art, the invention has the beneficial effects that:
1. compared with the traditional S3R and S4R mode full-regulation framework, the bus full-regulation framework has the advantages of simple structure, high specific power, flexible configuration and the like, can realize bus full-regulation and simultaneously furthest utilize sunlight to generate electricity, and increases the generating efficiency of the system.
2. Compared with the existing MPPT mode architecture, the technical scheme of the invention has the advantages that the charging and discharging module with the same hardware structure is arranged at the storage battery end, the bus full-adjustment function is realized, and meanwhile, the distributed system architecture is provided, so that the reliability of the system is greatly enhanced.
3. The energy storage battery adopting the technical scheme of the invention adopts a 21700 lithium ion battery, has the advantage of high specific energy compared with a 18650 battery adopted in the prior art, and can reduce the weight of the storage battery and reduce the satellite launching cost under the same energy requirement.
4. The power supply system is a distributed power supply system, the power generation units and the energy storage battery pack are connected to the bus through the power electronic device, and the power generation units and the energy storage battery pack are not influenced mutually, so that the power generation system can work normally without causing great influence on the system if a fault occurs and the power generation unit is isolated in time.
Drawings
FIG. 1 is a schematic circuit diagram of a power system according to the present invention;
fig. 2 is a schematic circuit diagram of the S3R power supply system;
fig. 3 is a schematic circuit diagram of the S4R power supply system;
fig. 4 is a schematic diagram of a MPPT half-regulation bus power supply circuit structure.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, 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 invention.
Example 1
Referring to fig. 1-4, the present invention provides a technical solution: a distributed low-orbit small satellite power supply system comprises a solar cell array, a photovoltaic adjusting unit, a storage battery pack, a charging and discharging adjusting module, a bus filtering module and an external load:
the photovoltaic adjusting unit and the charging and discharging adjusting module are provided with the same hardware circuit, and the injection software algorithms of the photovoltaic adjusting unit and the charging and discharging adjusting module are different;
the solar cell array adopts a modular subarray design, and each subarray is an independent power supply unit;
the storage battery pack adopts 21700 standard electric core with higher specific energy to combine into 10 groups of battery packs;
a capacitor module in the bus filtering module adopts a film capacitor with a self-healing function;
the solar cell array is electrically connected with the photovoltaic adjusting unit, the storage battery pack is electrically connected with the charge-discharge adjusting module, the photovoltaic adjusting unit and the charge-discharge adjusting module are both electrically connected with a system bus, and the system bus is electrically connected with a bus load and a bus capacitor to form a power supply system.
Specifically, the solar cell array adopts high-efficiency film type gallium arsenide solar cell monomers, each high-efficiency film type gallium arsenide solar cell monomer is combined into small assemblies with required voltage and current in a imbricated splicing mode, and the small assemblies form a sub-array through a series-parallel circuit;
the solar cell array comprises 10 solar cell sub-arrays, each sub-array is provided with one photovoltaic adjusting unit to form a power generation unit, and each power generation unit is independently connected to the system bus.
Specifically, the photovoltaic adjusting unit circuit unit comprises a DCDC boost circuit and a DSP control circuit;
the input end of the photovoltaic adjusting unit is a solar cell subarray, and the output end of the photovoltaic adjusting unit is a system bus;
the state of a DCDC circuit switching tube is regulated in a PWM mode so as to realize the maximum power tracking of the solar cell array and utilize the solar energy to the maximum extent;
and each DSP control circuit is respectively corresponding to one DCDC circuit to carry out closed-loop control.
Specifically, the DSP control circuit comprises a TMS320F2808 controller and a MOSFET drive chip, and the TMS320F2808 controller and the MOSFET drive chip are injected with an MPPT algorithm to realize duty ratio adjustment of a switching tube of the DCDC circuit, so that the output voltage of the solar cell array is adjusted, and the maximum power of the solar cell array is tracked;
the MPPT algorithm adopts a disturbance observation method and a genetic algorithm dual-mode control, when the change of the maximum power point is small, the maximum power point is tracked by a small step disturbance observation method, when the external change is not large, the difference of the maximum power points is not large, the former maximum power point is reserved, the next round of tracking is directly carried out, and when the external change is large, the tracking is carried out according to the disturbance method.
Specifically, the storage battery pack is formed by combining 21700 standard battery cores with higher specific energy in a mode of 2 parallel 12 series connection, the rated voltage of the battery pack is 42V, and the capacity of the battery pack is 8.4Ah, and each battery pack is provided with a charging and discharging adjusting module to form a power supply module access system bus.
Specifically, the charging and discharging regulation module comprises a DCDC circuit capable of boosting and reducing voltage and a DSP control circuit;
one end of the charge-discharge adjusting module is connected with the storage battery pack, and the other end of the charge-discharge adjusting module is connected with a system circuit bus;
the control function is realized by injecting an algorithm into the charging and discharging regulation module, the state of the switching tube is regulated according to external requirements, when the main topology is in a voltage reduction mode, the charging device is used for charging the storage battery by taking power from the system bus, and when the main topology is in a voltage increase mode, the discharging regulator is used for discharging the system bus and regulating the voltage of the system bus;
the charge and discharge regulation module adopts a PI double closed-loop control method, and comprises two control parts: current inner loop PI control and voltage outer loop PI control;
controlling the current inner ring: the current flowing through the inductor is the current with given amplitude and phase through the means of current negative feedback;
voltage outer loop control: negative feedback of voltage is introduced, so that the voltage on the direct current side is stabilized to be a given value, and the system bus voltage is adjusted.
Specifically, each solar cell sub-array in the solar cell array is connected to a system bus through a photovoltaic adjusting unit, each battery pack is connected to the system bus through a charging and discharging adjusting module, the two modules form a distributed power system framework, and each power supply unit is independent.
Specifically, the bus filter module is connected between a positive electrode and a negative electrode of the bus, and filters current in the system bus based on internal capacitance to shield unnecessary alternating current components and smooth direct current;
the film type capacitor adopts a polypropylene film as a medium, a layer of thin metal is evaporated on the surface of the polypropylene film as a conductive electrode, when an overhigh voltage is applied, the electric weakness of the polypropylene film is broken down, the resistance of a breakdown point is obviously reduced, the density of the flowing current is sharply increased, a metalized coating generates high heat, a metal conductor around the breakdown point is quickly evaporated and dissipated to form a blank area of the metal coating, the breakdown point automatically recovers insulation, and the reliability of a power supply system is improved.
Specifically, the load comprises two parts:
one is an on-satellite payload that can accommodate a dc 42V supply voltage;
the other is a satellite power distributor which mainly has the function of converting a 42V direct current bus into different output voltages so as to meet the requirements of other loads on the satellite;
meanwhile, the load can meet the energy balance of the whole satellite power supply system by adjusting the power requirement.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.

Claims (9)

1. The utility model provides a distributing type low orbit microsatellite electrical power generating system, includes solar cell array, photovoltaic adjusting unit, storage battery, charge-discharge adjusting module, generating line filter module and external load, its characterized in that:
the photovoltaic adjusting unit and the charging and discharging adjusting module are provided with the same hardware circuit, and the injection software algorithms of the photovoltaic adjusting unit and the charging and discharging adjusting module are different;
the solar cell array adopts a modular subarray design, and each subarray is an independent power supply unit;
the storage battery pack adopts 21700 standard electric core with higher specific energy to combine into 10 groups of battery packs;
a capacitor module in the bus filter module adopts a film capacitor with a self-healing function;
the solar cell array is electrically connected with the photovoltaic adjusting unit, the storage battery pack is electrically connected with the charge-discharge adjusting module, the photovoltaic adjusting unit and the charge-discharge adjusting module are electrically connected into a system bus, and the system bus is electrically connected with a bus load and a bus capacitor to form a power supply system.
2. The distributed low earth orbit microsatellite power supply system as claimed in claim 1 wherein: the solar cell array adopts high-efficiency film type gallium arsenide solar cell monomers, each high-efficiency film type gallium arsenide solar cell monomer is combined into small assemblies with required voltage and current in a imbricated splicing mode, and the small assemblies form a sub-array through a series-parallel circuit;
the solar cell array comprises 10 solar cell sub-arrays, each sub-array is provided with one photovoltaic adjusting unit to form a power generation unit, and each power generation unit is independently connected to the system bus.
3. The distributed low earth orbit microsatellite power supply system according to claim 1 wherein: the photovoltaic adjusting unit circuit unit comprises a DCDC voltage-boosting circuit and a DSP control circuit;
the input end of the photovoltaic adjusting unit is a solar cell subarray, and the output end of the photovoltaic adjusting unit is a system bus;
the state of a DCDC circuit switching tube is regulated in a PWM mode so as to realize the maximum power tracking of the solar cell array and utilize the solar energy to the maximum extent;
and each DSP control circuit is respectively corresponding to one DCDC circuit to carry out closed-loop control.
4. A distributed low earth orbit microsatellite power supply system as claimed in claim 3 wherein: the DSP control circuit comprises a TMS320F2808 controller and a MOSFET drive chip, and the TMS320F2808 controller and the MOSFET drive chip are injected with an MPPT algorithm to realize duty ratio adjustment of a switching tube of the DCDC circuit, so that the output voltage of the solar cell array is adjusted, and the maximum power of the solar cell array is tracked;
the MPPT algorithm adopts a disturbance observation method and a genetic algorithm dual-mode control, when the change of the maximum power point is small, the maximum power point is tracked by a small step disturbance observation method, when the external change is small, the difference of the maximum power points is small, the former maximum power point is reserved and directly enters the next round of tracking, and when the external change is large, the tracking is carried out according to the disturbance method.
5. The distributed low earth orbit microsatellite power supply system as claimed in claim 1 wherein: the storage battery pack is formed by combining 21700 standard battery cores with higher specific energy in a mode of 2 parallel 12 strings, the rated voltage of the battery pack is 42V, and the capacity of the battery pack is 8.4Ah, and each battery pack is provided with a charging and discharging adjusting module to form a power supply module access system bus.
6. The distributed low earth orbit microsatellite power supply system according to claim 1 wherein: the charging and discharging regulation module comprises a DCDC circuit capable of increasing and decreasing voltage and a DSP control circuit;
one end of the charge-discharge adjusting module is connected with the storage battery pack, and the other end of the charge-discharge adjusting module is connected with a system circuit bus;
the control function is realized by injecting an algorithm into the charging and discharging regulation module, the state of the switching tube is regulated according to external requirements, when the main topology is in a voltage reduction mode, the charging device becomes a charger, the system bus takes electricity to charge the storage battery, and when the main topology is in a voltage boosting mode, the charging device becomes a discharging regulator, the battery discharges electricity to the system bus, and the voltage of the system bus is regulated;
the charge and discharge regulation module adopts a PI double closed-loop control method, and comprises two control parts: current inner loop PI control and voltage outer loop PI control;
current inner loop control: the current flowing through the inductor is the current with given amplitude and phase through the means of current negative feedback;
voltage outer loop control: negative feedback of voltage is introduced, so that the voltage on the direct current side is stabilized to be a given value, and the system bus voltage is adjusted.
7. The distributed low earth orbit microsatellite power supply system according to claim 1 wherein: each solar cell sub-array in the solar cell array is connected to the system bus through the photovoltaic adjusting unit, each battery pack is connected to the system bus through the charging and discharging adjusting module, the two modules form a distributed power system framework, and each power supply unit is independent.
8. The distributed low earth orbit microsatellite power supply system according to claim 1 wherein: the bus filtering module is connected between the positive electrode and the negative electrode of the bus, and filters current in the system bus based on internal capacitance to shield unnecessary alternating current components and smooth direct current;
the film type capacitor adopts a polypropylene film as a medium, a layer of thin metal is evaporated on the surface of the polypropylene film as a conductive electrode, when an overhigh voltage is applied, the electric weakness of the polypropylene film is broken down, the resistance of a breakdown point is obviously reduced, the density of the flowing current is sharply increased, so that the metalized coating generates high heat, a metal conductor around the breakdown point is quickly evaporated and dissipated to form a blank area of the metal coating, the breakdown point automatically recovers insulation, and the reliability of a power supply system is improved.
9. The distributed low earth orbit microsatellite power supply system according to claim 1 wherein: the load comprises two parts:
one is an on-satellite payload that can accommodate a dc 42V supply voltage;
the other is a satellite power distributor which mainly has the function of converting a 42V direct current bus into different output voltages so as to meet the requirements of other loads on the satellite;
meanwhile, the load can meet the energy balance of the whole satellite power supply system by adjusting the power requirement.
CN202210366718.7A 2022-04-08 2022-04-08 Distributed low-orbit small satellite power supply system Pending CN114784939A (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN116454979A (en) * 2023-06-14 2023-07-18 北京钧天航宇技术有限公司 Distributed power supply system of modularized satellite, application method and electronic equipment

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN116454979A (en) * 2023-06-14 2023-07-18 北京钧天航宇技术有限公司 Distributed power supply system of modularized satellite, application method and electronic equipment

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