CN112865242B - Multi-energy interconnection power supply energy control system and method for satellite power supply system - Google Patents
Multi-energy interconnection power supply energy control system and method for satellite power supply system Download PDFInfo
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- CN112865242B CN112865242B CN202110108441.3A CN202110108441A CN112865242B CN 112865242 B CN112865242 B CN 112865242B CN 202110108441 A CN202110108441 A CN 202110108441A CN 112865242 B CN112865242 B CN 112865242B
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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
- H02J7/0063—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with circuits adapted for supplying loads from the battery
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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
- H02J7/00306—Overdischarge protection
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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
- H02J7/0047—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with monitoring or indicating devices or circuits
- H02J7/0048—Detection of remaining charge capacity or state of charge [SOC]
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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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- 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
A multi-energy interconnection power supply energy control system and method for a satellite power supply system comprises the following steps: the system comprises a bus power supply multi-energy interconnection power supply device, a multi-energy interconnection energy management device and a satellite power supply heat management device, wherein the multi-energy interconnection energy management device is used for integrally managing power distribution and charging/discharging control of each power supply device submodule, and the satellite power supply heat management device is used for carrying out low-temperature cold start preheating and high-temperature heat dissipation control on the multi-energy interconnection power supply device submodule. The invention can effectively prolong the service life and safety of each capacity/energy storage power supply subsystem component in the satellite power supply system.
Description
Technical Field
The invention relates to a technology in the field of satellite power supply, in particular to a multi-energy interconnection power supply energy control system and method for a satellite power supply system.
Background
Satellite power systems face extreme environmental challenges of extreme temperature, vacuum heat dissipation, intense radiation, and the like, and can only rely on batteries and fuel cell stacks to provide power during terrestrial photography. Therefore, the power supply system of the geosynchronous orbit satellite has extremely high requirements on the reliability of a power supply system and the high efficiency of a power distribution system so as to meet the long-term on-orbit operation requirement of the satellite. However, management and control of each sub-module in the conventional satellite power supply system are performed independently, and the application of the energy management technology based on multi-energy interconnection power supply to the satellite power supply system is still in a blank state.
Disclosure of Invention
The invention provides a multi-energy interconnection power supply energy control system and method of a satellite power supply system aiming at the practical application of the on-orbit satellite power supply system for supplying power by using multiple energy sources, and the system and method can effectively prolong the service life and safety of each energy production/energy storage power supply subsystem component in the satellite power supply system.
The invention is realized by the following technical scheme:
the invention relates to a multi-energy interconnection power supply energy control system of a satellite power supply system, which comprises: the system comprises a bus power supply multi-energy interconnection power supply device, a multi-energy interconnection energy management device and a satellite power supply heat management device, wherein the multi-energy interconnection energy management device is used for integrally managing power distribution and charging/discharging control of each power supply device submodule, and the satellite power supply heat management device is used for carrying out low-temperature cold start preheating and high-temperature heat dissipation control on the multi-energy interconnection power supply device submodule.
The multi-energy source interconnection power supply device comprises: solar photovoltaic cell array, shunt regulator, oxyhydrogen fuel cell stack and its discharge regulator, nickel cobalt lithium manganate energy type group battery, lithium titanate power type group battery and two lithium ion battery group corresponding charge/discharge regulator and direct current bus that the energy management device that interconnects with the multipotency source respectively in order to realize power collaborative distribution, wherein: the solar photovoltaic cell array is connected in parallel on a direct current bus in an illumination period, part of generated electric energy supplements and charges the lithium nickel cobalt manganese oxide energy type battery pack and the lithium titanate power type battery pack, when the generated electric energy overflows, the electric energy is dissipated through a shunt regulator connected in parallel on the direct current bus, and the electric energy is disconnected with the direct current bus in a ground shadow period; the nickel cobalt lithium manganate energy type battery pack is charged through a solar photovoltaic array in the illumination period, and outputs power to maintain the voltage of a direct-current bus in the ground shadow period; the lithium titanate power type battery pack outputs supplementary power when the power demand is higher than the output power of the photovoltaic array in the illumination period and the short-time load, and the lithium nickel cobalt manganese oxide power type battery pack supply power for a direct-current bus together in the shadow period; the hydrogen-oxygen fuel cell stack is connected with the direct current bus through the discharge regulator, and supplies power to the direct current bus together with the lithium ion battery pack during the earth shadow period and when the satellite load needs long-time high power, and supplements and charges the lithium ion battery pack.
The shunt regulator dissipates the excess energy overflowing from the solar photovoltaic cell array during the illumination period of the satellite based on a sequential switch shunt regulation technology (S4R).
The charging/discharging regulator is based on a bidirectional DC/DC converter and a closed-loop PI control principle and is used for controlling input/output power and charging/discharging safety protection of the nickel cobalt lithium manganate energy type battery pack and the lithium titanate power type battery pack.
The discharge regulator of the hydrogen-oxygen fuel cell stack is based on a DC/DC converter with a unidirectional Buck structure and is used for regulating the output power of the fuel cell stack.
The multi-energy source interconnection energy management device comprises: the energy management system comprises four sensor measuring modules connected with a power supply device productivity/energy storage submodule, four distributed control modules connected with charging/discharging regulators and shunt regulators and a multi-energy interconnection energy comprehensive management module cooperating with the distributed control modules, wherein: the sensor measuring modules of the solar photovoltaic cell array, the nickel cobalt lithium manganate energy type battery pack, the lithium titanate power type battery pack and the hydrogen-oxygen fuel cell stack carry out noise filtering and preprocessing on the collected signals of each productivity/energy storage submodule and feed the signals back to each distributed control module; the distributed control modules of the shunt regulator, the nickel cobalt lithium manganate energy type battery pack charging/discharging regulator, the lithium titanate power type battery pack charging/discharging regulator and the oxyhydrogen fuel cell stack power regulator adopt Pulse Width Modulation (PWM) to control the charging/discharging regulators so as to realize closed-loop control on bus voltage and output power of each productivity/energy storage sub-module, and meanwhile, the distributed control modules estimate state parameters of each productivity/energy storage module based on measurement signals and feed the state parameters back to the multi-energy interconnection energy comprehensive management module; the multi-energy interconnection energy comprehensive management module realizes the cooperative management and control of each distributed control module based on two sets of fuzzy logic algorithms and rule constraints, and deduces the temperature control range of the satellite power supply heat management device according to the fuzzy algorithm.
The state parameters comprise: fuel cell stack operating efficiency, state of charge (SoC) of two lithium ion battery packs.
The satellite power supply heat management device monitors the overall temperature of the satellite power supply system in an illumination period and a ground shadow period, and specifically comprises: nickel cobalt lithium manganate energy type group battery, lithium titanate power type group battery and oxyhydrogen fuel cell's thermal management module, wherein: preheating heat management modules of the nickel cobalt lithium manganate energy type battery pack and the lithium titanate power type battery pack before charging in a lighting period, carrying out cold start preheating on the two batteries in a shadow period, and maintaining the operating temperatures of the nickel cobalt lithium manganate energy type battery pack and the lithium titanate power type battery pack between-20 ℃ and 50 ℃; the thermal management module of the hydrogen-oxygen fuel cell preheats the cold start of the fuel cell.
Technical effects
The invention integrally solves the defects that the conventional satellite power management system and method cannot realize multi-energy interconnection and cooperative power supply, the problem of complexity of cooperative management and control of multi-energy interconnection power supply of a geosynchronous orbit satellite power system, the problem of cooperative power allocation of multi-energy interconnection in the satellite power system and the problem of joint management and control of the electric heating state of a sub-module of the satellite power system.
Compared with the prior art, the distributed control technology and the hierarchical supervision management technology are fused and applied, and the comprehensive multi-energy interconnection power supply energy management method based on the cooperative control rule and the fuzzy logic algorithm is established, so that the service life and the reliability of the power supply system of the on-orbit satellite are effectively prolonged, the advantage of complementation of multi-energy characteristics is reflected, and the robustness of the power supply system is improved.
Drawings
FIG. 1 is a schematic structural view of the present invention;
in the figure: the solar photovoltaic system comprises a solar photovoltaic array 1, a shunt regulator 2, a lithium titanate battery pack charging/discharging regulator 3, a lithium titanate power battery pack 4, a satellite thermal management device 5, a multi-energy interconnection power supply energy management device 6, a nickel cobalt lithium manganate battery pack charging/discharging regulator 7, a nickel cobalt lithium manganate energy battery pack 8, a fuel cell stacking electricity regulator 9, a hydrogen-oxygen fuel cell stack 10, a satellite electricity load 11, a power control signal 12, a direct-current bus 13 and a temperature control signal 14;
FIG. 2 is a schematic diagram of a multi-energy-source interconnection power supply energy management and control strategy;
in the figure: the method comprises the following steps of respectively distributing power supplied by a nickel cobalt lithium manganate battery pack and a lithium titanate battery pack to a direct-current bus load in a shadow period and distributing power charged by the nickel cobalt lithium manganate battery pack and a fuel battery pack to the lithium titanate battery pack when the SoC of the lithium titanate battery pack is lower than 20% in the shadow period; the first set of fuzzy logic algorithm has three input quantities, namely load demand power and SoC of two lithium ion battery packs, and the output quantity is the output power distribution ratio of the two lithium ion battery packs; the second set of fuzzy logic algorithm has four input quantities, namely load required power, lithium titanate battery pack charging required power, nickel cobalt manganese acid lithium battery pack SoC and fuel cell stack working efficiency, after normalization and fuzzification processing, the corresponding fuzzy output is calculated by an inference machine according to a preset fuzzy rule, and then defuzzification and denormalization processing are carried out to obtain the optimized power ratio of the fuel cell stack to the lithium titanate battery pack charging.
Detailed Description
As shown in fig. 1, the system for controlling energy supplied by interconnected multiple energy sources of a satellite power supply system according to this embodiment includes: a solar photovoltaic cell array 1, a lithium titanate power type battery pack 4, a nickel cobalt lithium manganate energy type battery pack 8 and an oxyhydrogen fuel cell stack 10; the multi-energy-source interconnection power distribution module comprises a shunt regulator 2, a first charging/discharging regulator 3, a second charging/discharging regulator 7 and a discharging regulator 9, wherein: the lithium titanate power battery pack 4 and the nickel cobalt lithium manganate energy battery pack 8 are respectively connected with a direct current bus 13 through a charging/discharging regulator 3 and a charging/discharging regulator 7, and the hydrogen-oxygen fuel cell stack is connected with the direct current bus 13 through a discharging regulator 9; the power output of each distributed regulator 2, 3, 7 and 9 of the multi-energy interconnection power supply energy management device 6 is controlled to maintain the voltage of a direct current bus 13; the satellite thermal management device 5 receives the temperature control signal sent by the multi-energy interconnected power supply energy management device 6, and thermally manages the lithium titanate power type battery pack 4, the nickel cobalt lithium manganate energy type battery pack 8 and the hydrogen-oxygen fuel cell stack 10.
The embodiment relates to a control method of the system, which comprises the following two links which are circularly and alternately realized, and specifically comprises the following steps:
(1) during the illumination period: the solar photovoltaic cell array 1 is directly connected in parallel with a direct current bus 13 to supply power to a satellite power load 11, and meanwhile, the solar photovoltaic cell array 1 charges a lithium titanate power type battery pack 4 and a nickel cobalt manganese acid lithium battery pack 8; when the output electric energy of the solar photovoltaic cell array 1 overflows, the electric energy is dissipated through the current divider 2; when the required power of the satellite electric load 11 is higher than the output power of the solar photovoltaic cell array 1, the lithium titanate power type battery pack 4 supplies power to maintain the voltage of the dc bus 13, and the nickel cobalt lithium manganate energy type battery pack 8 and the oxyhydrogen fuel cell stack 10 are used as the electric storage energy storage modules in the shadow period to not supply power to the dc bus 13.
(2) In the shadow period: the solar photovoltaic cell array 1 and the shunt regulator 2 are disconnected from the direct current bus 13; the nickel cobalt lithium manganate energy type battery pack 8 and the lithium titanate power type battery pack 4 preferentially supply power to the direct current bus 13; the hydrogen-oxygen fuel cell stack 10 supplements the power supply.
The comprehensive multi-energy interconnection energy management module realizes the cooperative management and control of each distributed control module based on two sets of fuzzy logic algorithms and rule constraints, wherein:
the rule constraint comprises:
a first rule: in the illumination period, the solar photovoltaic array outputs full power and preferentially charges the nickel cobalt lithium manganate energy type battery pack; when the SoC of the lithium nickel cobalt manganese oxide energy type battery pack reaches 90%, the solar photovoltaic array independently charges the lithium titanate power type battery pack until the SoCs of the two lithium ion battery packs reach 90%, and then the two lithium ion battery packs are fully charged together; electric energy overflowing from the solar photovoltaic array is dissipated through the shunt regulator.
Rule two: in the illumination period, when the temperature of the nickel cobalt lithium manganate energy battery pack and the lithium titanate power battery pack is lower than 0 ℃, charging is forbidden to protect the batteries, the two battery packs are heated to 10 ℃ through a satellite thermal management device and can be charged, and the charging temperature is maintained between 10 ℃ and 25 ℃.
Rule three: in the illumination period, the lithium nickel cobalt manganese oxide energy type battery pack and the fuel cell stack do not supply power to the direct current bus, and when the satellite power load has a short-term high-power requirement, the lithium titanate power type battery pack supplies power to the satellite load to maintain the bus voltage.
Rule four: in the shadow period, the nickel cobalt lithium manganate energy type battery pack and the lithium titanate power type battery pack preferentially supply power for the load, the power output ratios of the nickel cobalt lithium manganate energy type battery pack and the lithium titanate power type battery pack are determined based on a fuzzy logic algorithm according to state parameters of the two lithium ion battery packs, and when the two lithium ion battery packs cannot supply power timely due to temperature constraint, the fuel cell stack preferentially supplies power for the satellite load to maintain the voltage of a direct current bus.
Rule five: in the shadow period, when the SoC of the lithium titanate power type battery pack is lower than 20%, the lithium titanate power type battery pack is charged by the fuel cell stack and the nickel cobalt lithium manganate energy type battery pack, the charging power distribution is determined by a fuzzy logic algorithm so as to ensure that the fuel cell stack operates in a high-efficiency interval, and the fuel cell stack is closed when the SoC is recovered to 80%.
Rule six: in the shadow period, the operating temperature of the nickel cobalt lithium manganate energy battery pack and the lithium titanate power battery pack is controlled between-20 ℃ and 50 ℃, when the temperature of the two lithium ion battery packs is lower than-20 ℃, discharging is prohibited to avoid overdischarging of the battery packs, the batteries can be discharged again after being preheated to more than 0 ℃, and a fuel cell stack supplies power to a satellite power load during the preheating period.
And designing two power distribution intelligent algorithms according to the cooperative control rule. The invention selects the algorithm based on the fuzzy logic principle design so as to realize the high-efficiency control by utilizing the hardware circuit consisting of the DSP chip.
As shown in fig. 2, the two sets of fuzzy logic algorithms include: the first set of fuzzy logic algorithm calculates the output power distribution of the nickel cobalt lithium manganate energy type battery pack and the lithium titanate power type battery pack in the shadow period, and has three input quantities: the power distribution method comprises the steps that power is required by a satellite power load, the nickel cobalt lithium manganate energy type battery pack SoC and the lithium titanate power type battery pack SoC, and the output quantity is the power distribution ratio of the two lithium ion battery packs. The second set of fuzzy logic algorithm calculates the power distribution of the lithium nickel cobalt manganese oxide battery pack and the fuel cell stack to the lithium titanate battery pack when the SoC of the lithium titanate battery pack is lower than 20% in the terrestrial shadow period, and has four input quantities: the output quantity is the optimized power ratio of the fuel cell stack to the lithium titanate battery pack charging. Both algorithms are constrained by the rule four, the rule five and the rule six.
The foregoing fuzzy logic algorithm will be the principle: after normalization and fuzzification processing of input quantity, a corresponding fuzzy output is calculated by an inference machine according to a preset fuzzy rule, and finally an accurate result is output after defuzzification and denormalization processing.
In a fuzzy logic algorithm: the discourse domain of each input and output variable is as follows:
the power demand of the satellite electric load is as follows: NB, NM, NS, ZE, PS, PM, PB
Lithium nickel cobalt manganese oxide energy type battery pack SoC: LE, ME, HE
Lithium titanate power type battery pack SoC: LE, ME, HE
The lithium titanate battery pack requires power for charging: LE, ME, HE
Fuel cell stack operating efficiency: LE, ME, HE
The lithium nickel cobalt manganese oxide battery pack has the following power ratio: NB, NS, ZE, PS, PB
The power supply ratio of the fuel cell stack to the lithium titanate battery pack is as follows: NB, NS, ZE, PS, PB
Fuzzy logic rules take the form of "IF-THEN", i.e.:
control rule of fuzzy algorithm 1 #:
Fuzzy Rule 2 IF (power demand of satellite electric load is NM, and lithium nickel cobalt manganese acid energy type battery pack Soc is HE, and lithium titanate power type battery pack Soc is LE) THEN (lithium nickel manganese acid battery pack power ratio is PB)
……
Fuzzy Rule 63 IF (power demand of satellite load is PB, and lithium nickel cobalt manganese acid energy type battery pack Soc is LE, and lithium titanate power type battery pack Soc is HE) THEN (lithium nickel manganese acid battery pack power ratio is NB)
The fuzzy logic algorithm rules described above are 63, and the relation between fuzzy statements is "or".
Control rule of fuzzy algorithm 2 #:
fuzzy Rule 1: IF (required power of satellite load is NB, required power of lithium titanate battery pack charging is LE, lithium nickel cobalt manganese oxide energy type battery pack SoC is HE, working efficiency of fuel cell stack is LE) THEN (power supply ratio of lithium titanate battery pack of fuel cell stack is NB)
……
Fuzzy Rule 189: IF (power demand of satellite electric load is PB, power demand of charging lithium titanate battery pack is HE, and lithium nickel cobalt manganese oxide energy battery pack SoC is LE, working efficiency of fuel cell stack is LE) THEN (power supply ratio of lithium titanate battery pack of fuel cell stack is PB)
The fuzzy logic algorithm rules described above are 189, and the relation between fuzzy statements is "or".
In a fuzzy logic algorithm: the membership function adopts a form of combining a triangle and a trapezoid.
In a fuzzy logic algorithm: and (3) defuzzification of fuzzy output is realized by adopting a gravity center method.
The foregoing embodiments may be modified in many different ways by those skilled in the art without departing from the spirit and scope of the invention, which is defined by the appended claims and all changes that come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein.
Claims (8)
1. A multi-energy interconnection power supply energy control system of a satellite power supply system is characterized by comprising: the system comprises a bus power supply multi-energy interconnection power supply device, a multi-energy interconnection energy management device and a satellite power supply heat management device, wherein the bus power supply multi-energy interconnection power supply device is used for supplying power to a bus, the multi-energy interconnection energy management device is used for integrally managing power distribution and charging/discharging control of each power supply device submodule, and the satellite power supply heat management device is used for carrying out low-temperature cold start preheating and high-temperature heat dissipation control on the multi-energy interconnection power supply device submodule;
the multi-energy source interconnection power supply device comprises: the solar photovoltaic cell array, the shunt regulator, the hydrogen-oxygen fuel cell stack and the discharge regulator thereof, the nickel-cobalt lithium manganate energy type battery pack, the lithium titanate power type battery pack, and the charging/discharging regulators and the direct current buses corresponding to the two lithium ion battery packs are respectively connected with the multi-energy interconnection energy management device to realize power cooperative distribution;
the multi-energy-source interconnection energy management device comprises: the system comprises four sensor measuring modules connected with a power supply device productivity/energy storage submodule, four distributed control modules connected with charging/discharging regulators and shunt regulators and a multi-energy interconnection energy comprehensive management module cooperating with the distributed control modules;
the satellite power supply heat management device monitors the overall temperature of the satellite power supply system in an illumination period and a ground shadow period, and specifically comprises: the lithium nickel cobalt manganese oxide energy battery pack, the lithium titanate power battery pack and the heat management module of the oxyhydrogen fuel cell;
the comprehensive management module for the energy of interconnection of the multiple energy sources realizes the cooperative management and control of each distributed control module based on two sets of fuzzy logic algorithms and rule constraints, and deduces the temperature control range of the thermal management device for the satellite power supply according to the fuzzy algorithm;
the solar photovoltaic cell array is connected in parallel to a direct current bus during the illumination period, part of generated electric energy supplements and charges the lithium nickel cobalt manganese oxide energy type battery pack and the lithium titanate power type battery pack, the generated electric energy is dissipated through a shunt regulator connected in parallel to the direct current bus when overflowing, and the generated electric energy is disconnected with the direct current bus during the ground shadow period; the nickel cobalt lithium manganate energy type battery pack is charged through a solar photovoltaic array in the illumination period, and outputs power to maintain the voltage of a direct current bus in the ground shadow period; the lithium titanate power type battery pack outputs supplementary power when the power demand is higher than the output power of the photovoltaic array in the illumination period and the short-time load, and the lithium nickel cobalt manganese oxide power type battery pack supply power for a direct-current bus together in the shadow period; the hydrogen-oxygen fuel cell stack is connected with the direct current bus through the discharge regulator, and supplies power to the direct current bus together with the lithium ion battery pack when the earth shadow period and the satellite load demand long-time high power, and supplements and charges the lithium ion battery pack;
the two sets of fuzzy logic algorithms comprise: the first set of fuzzy logic algorithm calculates the output power distribution of the nickel cobalt lithium manganate energy type battery pack and the lithium titanate power type battery pack in the shadow period, and has three input quantities: satellite power consumption load demand power, nickel cobalt lithium manganate energy type group battery SoC, lithium titanate power type group battery SoC, output volume are the power distribution ratio of two lithium ion battery groups, and when lithium titanate battery group SoC is less than 20% when nickel cobalt lithium manganate battery group and fuel cell pile are to the power distribution that lithium titanate battery group charges in the second set of fuzzy logic algorithm calculation shadow period, total four input: the load demand power, the lithium titanate battery pack charging demand power, the nickel cobalt manganese acid lithium battery pack SoC and the fuel cell stack working efficiency, and the output is the ratio of the optimized fuel cell stack to the lithium titanate battery pack charging power.
2. The satellite power system multi-energy interconnection power supply energy control system as claimed in claim 1, wherein the shunt regulator dissipates excess energy overflowing from the solar photovoltaic cell array during the illumination period of the satellite based on a sequential switch shunt regulation technique (S4R).
3. The satellite power system multi-energy interconnection power supply energy control system as claimed in claim 1, wherein the charge/discharge regulator is based on a bidirectional DC/DC converter and a closed-loop PI control principle, and is used for controlling input/output power and charge/discharge safety protection of the lithium nickel cobalt manganese oxide energy battery pack and the lithium titanate power battery pack.
4. The satellite power system multipotency source interconnection power supply energy control system of claim 1, wherein the discharge regulator of the oxyhydrogen fuel cell stack is based on a unidirectional Buck architecture DC/DC converter for regulating the output power of the fuel cell stack.
5. The satellite power system multi-energy interconnection power supply energy control system according to claim 1, wherein the sensor measurement modules of the solar photovoltaic cell array, the nickel cobalt lithium manganate energy type battery pack, the lithium titanate power type battery pack and the hydrogen-oxygen fuel cell stack perform noise filtering and preprocessing on the collected signals of each capacity/energy storage submodule and feed the signals back to each distributed control module; the distributed control modules of the shunt regulator, the nickel cobalt lithium manganate energy type battery pack charging/discharging regulator, the lithium titanate power type battery pack charging/discharging regulator and the oxyhydrogen fuel cell stack charging regulator adopt pulse width modulation to control the charging/discharging regulators so as to realize closed-loop control on bus voltage and output power of each productivity/energy storage sub-module, and meanwhile, the distributed control modules estimate state parameters of each productivity/energy storage module based on measurement signals and feed the state parameters back to the multi-energy interconnection energy comprehensive management module;
the state parameters comprise: fuel cell stack operating efficiency, state of charge (SoC) of two lithium ion battery packs.
6. The satellite power system multipotency source interconnection energy supply control system according to claim 5, wherein said regulation constraint includes:
rule one is as follows: in the illumination period, the solar photovoltaic array outputs full power and preferentially charges the nickel cobalt lithium manganate energy type battery pack; when the SoC of the lithium nickel cobalt manganese oxide energy type battery pack reaches 90%, the solar photovoltaic array independently charges the lithium titanate power type battery pack until the SoCs of the two lithium ion battery packs reach 90%, and then the two lithium ion battery packs are fully charged together; electric energy overflowing from the solar photovoltaic array is dissipated through the shunt regulator;
rule two: in the illumination period, when the temperature of the nickel cobalt lithium manganate energy battery pack and the lithium titanate power battery pack is lower than 0 ℃, charging is forbidden to protect the batteries, the two battery packs are heated to 10 ℃ through a satellite thermal management device to be charged, and the charging temperature is maintained between 10 ℃ and 25 ℃;
rule three: in the illumination period, the nickel cobalt lithium manganate energy type battery pack and the fuel cell stack do not supply power for a direct current bus, and when the satellite power load has short-term high-power demand, the lithium titanate power type battery pack supplies power for the satellite load to maintain the bus voltage;
and a fourth rule: in the shadow period, the nickel cobalt lithium manganate energy type battery pack and the lithium titanate power type battery pack preferentially supply power to a load, respective power output ratios are determined based on a fuzzy logic algorithm according to state parameters of the two lithium ion battery packs, and when the two lithium ion battery packs cannot supply power timely due to temperature constraint, a fuel cell stack preferentially supplies power to a satellite load to maintain the voltage of a direct current bus;
rule five: in the shadow period, when the SoC of the lithium titanate power type battery pack is lower than 20%, a fuel cell stack and a nickel cobalt lithium manganate energy type battery pack are used for charging the lithium titanate power type battery pack, the charging power distribution is determined by a fuzzy logic algorithm so as to ensure that the fuel cell stack operates in a high-efficiency interval, and the fuel cell stack is closed when the SoC is recovered to 80%;
rule six: in the earth shadow period, the operating temperature of the nickel cobalt lithium manganate energy battery pack and the lithium titanate power battery pack is controlled between-20 ℃ and 50 ℃, when the temperature of the two lithium ion battery packs is lower than-20 ℃, discharging is forbidden to avoid overdischarge of the battery packs, the batteries can be discharged again after being preheated to more than 0 ℃, and a fuel cell stack supplies power to a satellite power load during the preheating period.
7. The satellite power system multi-energy interconnection power supply energy control system according to claim 1, wherein the thermal management modules of the lithium nickel cobalt manganese oxide energy type battery pack and the lithium titanate power type battery pack are preheated before charging in a lighting period, and the two batteries are preheated in a cold start mode in a shadow period, and the operating temperatures of the lithium nickel cobalt manganese oxide energy type battery pack and the lithium titanate power type battery pack are maintained between-20 ℃ and 50 ℃; the thermal management module of the hydrogen-oxygen fuel cell preheats the cold start of the fuel cell.
8. A multi-energy interconnection power supply energy control method of a satellite power supply system is applied to the multi-energy interconnection power supply energy control system of the satellite power supply system in any one of claims 1 to 7, and is characterized by comprising the following two links which are circularly and alternately realized, specifically:
(1) during the illumination period: the solar photovoltaic battery array is directly connected in parallel with the direct current bus to supply power for the satellite power load, and simultaneously charges the lithium titanate power battery pack and the nickel cobalt lithium manganate battery pack; when the output electric energy of the solar photovoltaic cell array overflows, the electric energy is dissipated through the shunt regulator; when the required power of the satellite electric load is higher than the output power of the solar photovoltaic cell array, the lithium titanate power type battery pack supplies power to maintain the voltage of the direct current bus, and the nickel cobalt lithium manganate energy type battery pack and the oxyhydrogen fuel cell stack are used as the electric storage energy storage module in the earth shadow period to not supply power to the direct current bus;
(2) in the shadow period: the solar photovoltaic cell array and the shunt regulator are disconnected from the direct current bus; the nickel cobalt lithium manganate energy type battery pack and the lithium titanate power type battery pack preferentially supply power for a direct-current bus; the hydrogen-oxygen fuel cell stack supplements power supply.
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