Power supply method, system and equipment for three-satellite combination of medium-orbit satellites and medium

Abstract

The invention belongs to the technical field of spacecraft power management, and particularly relates to a power supply method, system and device for a three-satellite combination of medium-orbit satellites and a medium, and the method comprises the steps: collecting the energy state information and load demand information of three satellites in real time, the energy state information comprises output power of a solar cell array of each satellite, residual electric quantity of a storage battery and bus voltage, and the load demand information comprises current power demands of loads with different priorities on each satellite; collaborative decision making is carried out based on the energy state information and the load demand information, global control instructions are generated and issued, and the global control instructions at least comprise a dynamic voltage regulation instruction, a power distribution instruction and a switching trigger instruction; and each single satellite receives and executes the global control instruction so as to adjust the power supply state of the satellite in real time. According to the invention, the energy utilization efficiency of the assembly system is improved.

Description

Technical Field This disclosure belongs to the field of spacecraft power management technology, and in particular relates to a power supply method, system, equipment and medium for a medium-orbit satellite triple-cell combination. Background Technology

[0001] As the complexity of space missions increases, multi-satellite systems, especially medium-Earth orbit (MEO) satellite constellations, are gaining increasing attention due to their wide applications in navigation, communication, and remote sensing. In such systems, a reliable power supply is crucial to ensuring the continuous and stable operation of the satellite constellation and the successful completion of its intended missions.

[0002] Traditional satellite power management typically employs a single-satellite independent management model, where each satellite is independently responsible for its own energy harvesting (primarily through solar arrays), storage (through batteries), and distribution to meet its own load requirements. However, due to instantaneous differences in the space environment, attitude, and load demands of each satellite, some satellites may generate surplus power while others experience power shortages. This independent management model cannot achieve energy sharing and adjustment within the satellite constellation, resulting in low overall energy utilization efficiency. Traditional methods struggle to dynamically and adaptively adjust to the global energy situation of the three-satellite constellation, such as real-time adjustment of bus voltage, intelligent power allocation between satellites, and automatic power supply mode switching based on preset conditions. This leads to insufficient system capability to cope with complex operating conditions and unforeseen circumstances.

[0003] Therefore, there is an urgent need for a power supply management solution that can overcome the limitations of single-satellite energy management and achieve integrated, coordinated scheduling and optimized allocation of energy across the three-satellite complex, thereby improving the energy utilization efficiency, power supply reliability, and mission adaptability of the entire complex system. Summary of the Invention

[0004] To address the aforementioned issues, this disclosure provides a power supply method, system, device, and medium for a three-satellite combination in medium Earth orbit. By collecting and analyzing the energy status and load demand information of the three satellites in real time, it enables efficient sharing and intelligent allocation of energy within the combination, significantly improving the energy utilization efficiency of the combination system.

[0005] In a first aspect, this disclosure provides a method for powering a three-satellite array in medium Earth orbit, the method comprising, Real-time acquisition of energy status information and load demand information of three satellites. The energy status information includes the output power of the solar array of each satellite, the remaining power of the battery and the bus voltage. The load demand information includes the current power demand of different priority loads on each satellite. Based on the energy status information and the load demand information, a collaborative decision is made to generate and issue global control commands. The global control commands include at least dynamic voltage regulation commands, power allocation commands, and switching trigger commands. Each satellite receives and executes the global control command to adjust its power supply status in real time.

[0006] Furthermore, Real-time collection of payload requirements information for three satellites, specifically including: The priority of each load is determined based on the following criteria: Based on the operational requirements and mission objectives of the three-satellite combination in medium orbit, the priority of the load is divided from three core dimensions: functional necessity, mission relevance, and fault impact, and the priority division results are obtained. Based on the priority division results, current power demand data for loads with different priorities are collected.

[0007] Furthermore, The collaborative decision-making based on the energy status information and the load demand information specifically includes the following steps: The energy status information and the load demand information are integrated into a Samsung combined energy situation diagram; The system analyzes the energy status diagram of the Samsung system, continuously monitors the real-time bus voltage value of each satellite, compares it with a preset voltage threshold, and generates a dynamic voltage regulation command based on the voltage comparison result. Analyze the energy situation map of the Samsung complex to identify satellites with surplus power generation and satellites with shortage power generation, and generate power allocation instructions based on the identification results; The system analyzes the energy status diagram of the Samsung complex, monitors key trigger data in real time, compares the key trigger data with preset trigger data thresholds, and generates trigger commands based on the trigger comparison results.

[0008] Furthermore, The energy status information and the load demand information are integrated into a Samsung combined energy situation map, specifically including: The energy status information and load demand information of the three satellites were spatiotemporally aligned and fused to obtain fused data. A global energy supply and demand matrix is ​​constructed based on the fused data; Based on the global energy supply and demand matrix, the total energy supply capacity, total load demand, and real-time supply and demand difference of the Samsung complex are calculated and stored and updated in a visual data structure format to form the energy status map of the Samsung complex.

[0009] Furthermore, Dynamic voltage regulation commands are generated based on voltage comparison results, specifically including: The real-time bus voltage of each satellite is compared with the preset voltage threshold to obtain the comparison results and calculate the voltage deviation value. If the voltage deviation of a certain star bus exceeds the preset dead zone threshold, voltage regulation parameters are generated according to the preset deviation adjustment mapping table. Based on the voltage regulation parameters, a specific dynamic voltage regulation command is generated. The dynamic voltage regulation command includes at least the target satellite identifier, the target voltage value, and the voltage regulation rate, and specifies that the on-board power controller shall execute the dynamic voltage regulation command operation.

[0010] Furthermore, Power allocation instructions are generated based on the recognition results, specifically including: According to the energy status diagram of the Samsung system, satellites whose current power generation is greater than their total load demand are identified as satellites with power surplus, and satellites whose current power generation is less than their total load demand are identified as satellites with power shortage. A power allocation strategy is generated based on the identification results of surplus and shortage power generation satellites. Power allocation instructions are then generated according to the power allocation strategy. The power allocation instructions include the power output satellite, the power receiving satellite, the transmission power value, and the transmission path used.

[0011] Furthermore, Trigger commands are generated based on the trigger comparison results, specifically including: Continuously monitor key trigger data in the energy status diagram of the Samsung complex, including the remaining battery power of each satellite, the reduction in the output power of the solar array, and the global energy supply and demand difference; The key trigger data is compared with preset multi-level trigger thresholds; When the key trigger data exceeds the preset multi-level trigger threshold, a corresponding switching trigger instruction is generated.

[0012] Secondly, based on the same inventive concept, this disclosure provides a power supply system for a medium-Earth orbit satellite triple-cell assembly, the system comprising: The data acquisition module is used to collect the energy status information and load demand information of the three satellites in real time. The energy status information includes the output power of the solar array of each satellite, the remaining power of the battery and the bus voltage. The load demand information includes the current power demand of different priority loads on each satellite. The instruction generation module is used to make collaborative decisions based on the energy status information and the load demand information, generate and issue global control instructions, and the global control instructions include at least dynamic voltage regulation instructions, power allocation instructions and switching trigger instructions. The instruction execution module is used for each satellite to receive and execute the global control instructions in order to adjust the power supply status of the satellite in real time.

[0013] Thirdly, this disclosure also provides an electronic device, including a processor, a communication interface, a memory, and a communication bus, wherein the processor, the communication interface, and the memory communicate with each other through the communication bus; Memory, used to store computer programs; When the processor executes a program stored in memory, it implements the steps of any of the power supply methods for a medium-Earth orbit satellite triple-cell assembly as described above.

[0014] Fourthly, this disclosure also provides a computer storage medium, characterized in that the computer storage medium stores a computer program, which, when executed by a processor, implements the steps of any of the above-described methods for powering a medium-Earth orbit satellite triple-cell combination.

[0015] Compared with the prior art, this disclosure has the following advantages: 1. The power supply method for a three-satellite combination in medium orbit proposed in this disclosure achieves precise control of dynamic voltage regulation, on-demand power allocation, and rapid fault response by collecting and coordinating the energy status and load demand information of the three satellites in real time. This effectively solves the problems of low energy utilization and delayed supply and demand matching in the traditional single-satellite independent power supply mode. 2. This disclosure innovatively constructs a Samsung combined energy situation map, integrating scattered energy data into a visualized global model, enabling the power supply system to perceive the dynamic changes in the power generation capacity and load demand of each satellite in real time, providing data support for collaborative decision-making; 3. The priority load partitioning mechanism adopted by the system combines three dimensions: functional necessity, task relevance, and fault impact, to ensure continuous power supply to critical loads and significantly improve the mission reliability of the assembly in complex space environments. 4. Through multi-level trigger threshold design and closed-loop control of dynamic voltage regulation commands, this solution can automatically adapt to fluctuations in the output power of the solar array and changes in battery power, avoiding damage to the onboard equipment caused by overvoltage / undervoltage of the bus and extending the service life of the equipment.

[0016] Other features and advantages of this disclosure will be set forth in the description which follows, and will be apparent in part from the description, or may be learned by practicing the disclosure. The objects and other advantages of this disclosure may be realized and obtained by means of the structures pointed out in the description, claims and drawings. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments of this disclosure or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this disclosure. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0018] Figure 1 A schematic flowchart of a power supply method for a medium-Earth orbit satellite triple-cell assembly according to an embodiment of the present disclosure is shown; Figure 2 A structural block diagram of a power supply system for a medium-Earth orbit satellite triple-cell assembly according to an embodiment of the present disclosure is shown. Detailed Implementation

[0019] To make the objectives, technical solutions, and advantages of the embodiments of this disclosure clearer, the technical solutions of the embodiments of this disclosure will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this disclosure, and not all embodiments. Based on the embodiments of this disclosure, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this disclosure.

[0020] Figure 1 A schematic flowchart of a power supply method for a medium-Earth orbit satellite triple-cell assembly according to an embodiment of this disclosure is shown, as follows: Figure 1 As shown, an embodiment of this disclosure provides a power supply method for a three-satellite array in medium Earth orbit, comprising: S1, real-time acquisition of energy status information and load demand information of three satellites. The energy status information includes the output power of the solar array of each satellite, the remaining power of the battery and the bus voltage. The load demand information includes the current power demand of different priority loads on each satellite. In this embodiment of the disclosure, step S1 specifically includes: S11, based on the operational requirements and mission objectives of the three-satellite combination in medium orbit, prioritizes the load from three core dimensions: functional necessity, mission relevance, and fault impact, and obtains the priority classification results. S12, Based on the priority division results, collect the current power demand data of loads with different priorities.

[0021] In this disclosed embodiment, functional necessity refers to the impact of load interruption on the basic survivability of the satellite. If load interruption will lead to fatal problems such as satellite attitude instability, inter-satellite communication interruption, and power system paralysis, it is determined to be highly necessary; if it only affects non-core data acquisition or redundant functions, it is determined to be low necessary. Task relevance: refers to the degree of relevance between the load and the current core tasks of the Samsung complex (such as regional observation, data relay, etc.). The main loads that directly serve the core tasks (such as the main observation camera and the core data processing unit) are judged as having high relevance, while the loads that only serve auxiliary tasks (such as equipment self-test and redundant data backup) are judged as having low relevance. Fault impact: This refers to whether a load interruption will trigger a chain reaction of failures. If the interruption will cause damage or performance degradation to other critical loads (such as batteries or solar arrays), it is considered a high impact. If only its own function fails and there is no risk of a chain reaction, it is considered a low impact.

[0022] In this embodiment of the disclosure, the load is divided into three levels based on the above dimensions, and the specific rules are as follows: Level 1 loads: These loads meet the requirements of "high functional necessity + high mission relevance + high failure impact", including but not limited to inter-satellite telemetry and control systems, attitude and orbit control systems, battery management systems, and three-satellite combination coordination control units. These loads are "uninterruptible loads" for satellite operation and combination coordination, and their priority is fixed at the highest. Secondary loads: These loads meet all conditions except for "high functional necessity + high mission relevance + high failure impact" and "low functional necessity + low mission relevance + low failure impact". They include, but are not limited to, core scientific exploration payloads (such as target observation cameras), on-board data storage main units, solar array power regulation modules, and thermal control systems. These loads are directly related to core missions or key energy control and have a lower priority than primary loads. Level 3 loads: These loads meet the criteria of "low functional necessity + low mission relevance + low failure impact," including but not limited to redundant scientific exploration payloads, periodic self-test modules for onboard equipment, and non-critical redundant data transmission units. These loads can be temporarily interrupted during energy shortages and have the lowest priority.

[0023] S2, based on the energy status information and the load demand information, make collaborative decisions, generate and issue global control instructions, the global control instructions include at least dynamic voltage regulation instructions, power allocation instructions and switching trigger instructions; In this embodiment of the disclosure, step S2 specifically includes: S21, integrate the energy status information and the load demand information into a Samsung combined energy situation diagram; S22, Analyze the energy status diagram of the three-star combination, continuously monitor the real-time bus voltage value of each star, compare it with the preset voltage threshold, and generate a dynamic voltage regulation command based on the voltage comparison result; S23, Analyze the energy status map of the Samsung complex, identify satellites with surplus power generation and satellites with shortage power generation, and generate power allocation instructions based on the identification results; S24, Analyze the energy status diagram of the Samsung combination, monitor key trigger data in real time, compare the key trigger data with preset trigger data thresholds, and generate trigger commands based on the trigger comparison results.

[0024] In this embodiment of the disclosure, step S21 specifically includes: S211 performs spatiotemporal alignment and data fusion processing on the energy status information and load demand information of the three satellites to obtain fused data; S212, Construct a global energy supply and demand matrix based on the fused data; S213. Based on the global energy supply and demand matrix, calculate the total energy supply capacity, total load demand, and real-time supply and demand difference of the Samsung complex, and store and update them in a visual data structure format to form the energy status map of the Samsung complex.

[0025] In this embodiment of the disclosure, the spatiotemporal alignment processing of the collected energy status information and load demand information includes: unified timestamp and spatial coordinate reference processing to avoid data asynchrony; The data fusion processing of collected energy status information and load demand information includes: removing outliers and supplementing missing values ​​to improve data quality.

[0026] In this embodiment of the disclosure, the rows of the global energy supply and demand matrix represent three satellites, and the columns include the solar power output, remaining battery power, bus voltage, and current power demand of each priority load for each satellite.

[0027] In this embodiment of the disclosure, the total energy supply capacity is calculated from the amount of electricity that can be released by Samsung solar power and batteries; The total load requirement is calculated by summing the loads of each satellite. The real-time supply-demand gap is calculated by subtracting total load demand from total energy supply capacity.

[0028] In this embodiment of the disclosure, the visualization format may be such as a dynamic table, a line graph, etc.

[0029] In this embodiment of the disclosure, step S22 specifically includes: S221, compare the real-time bus voltage of each satellite with the preset voltage threshold, obtain the comparison result, and calculate the voltage deviation value. S222, If the voltage deviation of a certain star bus exceeds the preset dead zone threshold, the voltage regulation parameters are generated according to the preset deviation adjustment mapping table. S223, Based on the voltage regulation parameters, generate a specific dynamic voltage regulation command. The dynamic voltage regulation command includes at least the target satellite identifier, the target voltage value, and the voltage regulation rate, and specifies that the on-board power controller shall execute the dynamic voltage regulation command operation.

[0030] In this embodiment of the disclosure, the preset voltage threshold is 28V±5%.

[0031] In this embodiment of the disclosure, the preset dead zone threshold is ±0.5V. If the voltage is 27.8V, which is slightly lower than 28V, the deviation (-0.2V) is within the dead zone threshold, and the system will not issue a voltage adjustment command.

[0032] In this embodiment of the disclosure, a possible example of the preset deviation adjustment mapping table is shown in Table 1 below:

[0033] Table 1. Preset Deviation Adjustment Mapping Relationship In this embodiment of the disclosure, the DC / DC converter is used when it is necessary to increase or decrease the bus voltage; Power controller: When the voltage is too high and cannot be resolved by reducing solar output, it is used to consume excess energy, which is equivalent to "braking".

[0034] In this embodiment of the disclosure, a possible example of a dynamic voltage regulation command is {command type: dynamic voltage regulation, target; SAT-B, target voltage: 28.2V, voltage regulation rate: 0.2V / second, actuator: DC / DC main converter}.

[0035] In this embodiment of the disclosure, step S23 specifically includes: S231, Based on the energy status map of the Samsung combination, satellites whose current power generation is greater than their total load demand are identified as power-surplus satellites, and satellites whose current power generation is less than their total load demand are identified as power-shortage satellites. S232, generate a power allocation strategy based on the identification results of surplus power generation satellites and shortage power generation satellites, and generate a power allocation instruction according to the power allocation strategy. The power allocation instruction includes the power output satellite, the power receiving satellite, the transmission power value and the transmission path used.

[0036] In this embodiment of the disclosure, the power allocation strategy is to prioritize scheduling the real-time surplus solar power of satellites with surplus power generation and transmit it to satellites with power shortage through inter-satellite energy transmission links; when the real-time surplus solar power is insufficient, the redundant battery power of each satellite is called up in a preset order to supplement it.

[0037] In this embodiment of the disclosure, the transmission path settings typically include: Link status and capacity: Prioritize transmission paths that are in normal condition and have large available bandwidth. For example, if there are multiple inter-satellite links in the system, the one with the lowest current bit error rate and lightest load will be selected.

[0038] Path loss efficiency: When conditions permit, prioritize paths that are physically closer or have lower transmission losses to maximize energy transmission efficiency.

[0039] Load balancing: To avoid a single link being under high load for a long time, the system may poll or distribute the load among multiple available paths in a round-robin or proportional manner to achieve load balancing and improve the overall reliability of the system.

[0040] Fault isolation: If a path is diagnosed as faulty or degraded, it will be removed from the available paths, and the command will automatically specify an alternative path.

[0041] In this embodiment of the disclosure, step S24 specifically includes: S241, continuously monitor key trigger data in the energy status diagram of the Samsung combination, including the remaining battery power of each satellite, the reduction in the output power of the solar array, and the global energy supply and demand difference; S242, compare the key trigger data with a preset multi-level trigger threshold; S243, when the key trigger data exceeds the preset multi-level trigger threshold, generate the corresponding switching trigger instruction.

[0042] In this disclosed embodiment, the key triggering data includes three types of core parameters: Remaining battery charge for each satellite (if SOC < 25%, emergency power replenishment is required). The decrease in output power of the solar array (e.g., a decrease of more than 30% within 1 minute may indicate a malfunction); Global energy supply and demand imbalance (e.g., total supply < total demand 80% requires load reduction).

[0043] In this embodiment of the disclosure, the preset multi-level trigger thresholds include S3, each satellite receives and executes the global control command to adjust its power supply status in real time.

[0044] Specifically, an example of applying the above method can be: In this example, the collaborative decision-making module is deployed on satellite A as a global control node.

[0045] 1. Design of primary busbar power distribution for Star A: Satellite A has a primary bus voltage of 46V, and provides satellites B and C with a bus voltage of 42V through the power distribution system.

[0046] The maximum power requirement for satellites B and C is 950W, while the actual power consumption is 745W, leaving a power margin of 200W.

[0047] The design supports charging the batteries of Satellite B and Satellite C with a charging current of 2A, a charging power of 84W, and a remaining power margin of 121W.

[0048] 2. Bus voltage control: The power supply voltage for satellite A needs to be controlled to be greater than 43.5V at the input terminals of satellites B and C.

[0049] The opening time of the bus control switch is less than 10ms to reduce current surge.

[0050] Considering the impact of bus capacitors on the current surge during power-on and power-off cycles, a surge suppression circuit was designed to ensure smooth switching.

[0051] 3. Power distribution control design: When satellites B and C are operating independently, disconnect the power distribution switch to ensure safe isolation.

[0052] When the voltage (after the diode) from satellite A exceeds 42.5V, the use of external power from the solar cells and the discharge of the batteries of satellites B and C is prohibited, and satellite A shall provide power.

[0053] When the voltage of satellite B and satellite C (after the diode) is less than 42.5V, they are powered by a combination of external power from the solar cells of satellite B and satellite C and power from the battery discharge.

[0054] 4. Control based on the deployment status of the solar panels: In the active phase, the Samsung solar panels do not deploy and are all in internal power mode.

[0055] After the separation of the satellite and rocket is completed, the three satellites in the transfer segment remain in a combined state, with the sails of satellite A deployed and the sails of satellites B and C retracted.

[0056] Satellite A supplies power to satellites B and C. The bus voltage of satellite A is 46V, and the bus voltages of satellites B and C are 42V. The power controller of satellite A supplies power to satellites B and C respectively through a power distribution switch.

[0057] B / C Star Interface Design Specifications (including surge protection): 1. Four reverse voltage protection diodes (2DK7062T or 35CGQ100) are connected in parallel. Four TO-254 packages can be connected in parallel and mounted on the structure (heat dissipation 3.85W).

[0058] 2. The opening time of the bus control switch is less than 10ms, taking into account the current impact of the bus capacitor on the power-on and power-off.

[0059] 3. Design a switch control (surge suppression design) function to realize the power distribution control of BC satellite, and disconnect the power distribution switch when BC satellite is working independently.

[0060] 4. To maintain safety redundancy, the four diodes at the BC star terminal are selected with low resistance values.

[0061] A-Star Interface Design Specifications: 1. Power is supplied to A-star via isolation diode. 2. Inside satellite A, four parallel MOSFETs are used to power B and C respectively. Each MOSFET has an impedance of 0.1Ω and a current of 950W / 46V=20.7A. The voltage drop is 20.7A*0.1Ω / 4=0.52V, so the voltage at the power supply port is 45.48V.

[0062] Based on the above method, this disclosure also provides a power supply system for a three-satellite array for medium-Earth orbit satellites, corresponding to the above method. Figure 2 A structural block diagram of a power supply system for a medium-Earth orbit satellite triple-cell assembly according to an embodiment of this disclosure is shown. See also: Figure 2 As shown, the system includes, The data acquisition module 10 is used to collect the energy status information and load demand information of the three satellites in real time. The energy status information includes the output power of the solar array of each satellite, the remaining power of the battery and the bus voltage. The load demand information includes the current power demand of different priority loads on each satellite. The instruction generation module 20 is used to make collaborative decisions based on the energy status information and the load demand information, generate and issue global control instructions, and the global control instructions include at least dynamic voltage regulation instructions, power allocation instructions and switching trigger instructions. The instruction execution module 30 is used for each satellite to receive and execute the global control instructions in order to adjust the power supply status of the satellite in real time.

[0063] Based on the same inventive concept as the above disclosure, this disclosure also provides an electronic device. The electronic device of this disclosure includes at least one processor and at least one memory electrically connected to the processor. The memory is electrically connected to the processor, wherein the memory stores instructions executable by the at least one processor, which, when executed by the at least one processor, enables the at least one processor to perform the method described above.

[0064] It should be noted that the electrical connection between the above-mentioned units does not necessarily mean the connection between lines. The indirect connection method can be applied to the embodiments of this disclosure as long as it achieves the purpose of this disclosure.

[0065] Based on the same inventive concept, this disclosure also provides a computer storage medium storing a computer program, which, when executed by a processor, implements the steps of the above method.

[0066] Although the present disclosure has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present disclosure.

Claims

1. A power supply method for a three-satellite array in medium Earth orbit, characterized in that, The method includes, Real-time acquisition of energy status information and load demand information of three satellites. The energy status information includes the output power of the solar array of each satellite, the remaining power of the battery and the bus voltage. The load demand information includes the current power demand of different priority loads on each satellite. Based on the energy status information and the load demand information, a collaborative decision is made to generate and issue global control commands. The global control commands include at least dynamic voltage regulation commands, power allocation commands, and switching trigger commands. Each satellite receives and executes the global control command to adjust its power supply status in real time.

2. The method according to claim 1, characterized in that, Real-time collection of payload requirements information for three satellites, specifically including: The priority of each load is determined based on the following criteria: Based on the operational requirements and mission objectives of the three-satellite combination in medium orbit, the priority of the load is divided from three core dimensions: functional necessity, mission relevance, and fault impact, and the priority division results are obtained. Based on the priority division results, current power demand data for loads with different priorities are collected.

3. The method according to claim 2, characterized in that, The collaborative decision-making based on the energy status information and the load demand information specifically includes the following steps: The energy status information and the load demand information are integrated into a Samsung combined energy situation diagram; The system analyzes the energy status diagram of the Samsung system, continuously monitors the real-time bus voltage value of each satellite, compares it with a preset voltage threshold, and generates a dynamic voltage regulation command based on the voltage comparison result. Analyze the energy situation map of the Samsung complex to identify satellites with surplus power generation and satellites with shortage power generation, and generate power allocation instructions based on the identification results; The system analyzes the energy status diagram of the Samsung complex, monitors key trigger data in real time, compares the key trigger data with preset trigger data thresholds, and generates trigger commands based on the trigger comparison results.

4. The method according to claim 3, characterized in that, The energy status information and the load demand information are integrated into a Samsung combined energy situation map, specifically including: The energy status information and load demand information of the three satellites were spatiotemporally aligned and fused to obtain fused data. A global energy supply and demand matrix is ​​constructed based on the fused data; Based on the global energy supply and demand matrix, the total energy supply capacity, total load demand, and real-time supply and demand difference of the Samsung complex are calculated and stored and updated in a visual data structure format to form the energy status map of the Samsung complex.

5. The method according to claim 4, characterized in that, Dynamic voltage regulation commands are generated based on voltage comparison results, specifically including: The real-time bus voltage of each satellite is compared with the preset voltage threshold to obtain the comparison results and calculate the voltage deviation value. If the voltage deviation of a certain star bus exceeds the preset dead zone threshold, voltage regulation parameters are generated according to the preset deviation adjustment mapping table. Based on the voltage regulation parameters, a specific dynamic voltage regulation command is generated. The dynamic voltage regulation command includes at least the target satellite identifier, the target voltage value, and the voltage regulation rate, and specifies that the on-board power controller shall execute the dynamic voltage regulation command operation.

6. The method according to claim 5, characterized in that, Power allocation instructions are generated based on the recognition results, specifically including: According to the energy status diagram of the Samsung system, satellites whose current power generation is greater than their total load demand are identified as satellites with power surplus, and satellites whose current power generation is less than their total load demand are identified as satellites with power shortage. A power allocation strategy is generated based on the identification results of surplus and shortage power generation satellites. Power allocation instructions are then generated according to the power allocation strategy. The power allocation instructions include the power output satellite, the power receiving satellite, the transmission power value, and the transmission path used.

7. The method according to claim 6, characterized in that, Trigger commands are generated based on the trigger comparison results, specifically including: Continuously monitor key trigger data in the energy status diagram of the Samsung complex, including the remaining battery power of each satellite, the reduction in the output power of the solar array, and the global energy supply and demand difference; The key trigger data is compared with preset multi-level trigger thresholds; When the key trigger data exceeds the preset multi-level trigger threshold, a corresponding switching trigger instruction is generated.

8. A power supply system for a three-satellite array in medium Earth orbit, characterized in that, The system includes, The data acquisition module is used to collect the energy status information and load demand information of the three satellites in real time. The energy status information includes the output power of the solar array of each satellite, the remaining power of the battery and the bus voltage. The load demand information includes the current power demand of different priority loads on each satellite. The instruction generation module is used to make collaborative decisions based on the energy status information and the load demand information, generate and issue global control instructions, and the global control instructions include at least dynamic voltage regulation instructions, power allocation instructions and switching trigger instructions. The instruction execution module is used for each satellite to receive and execute the global control instructions in order to adjust the power supply status of the satellite in real time.

9. An electronic device, characterized in that, It includes a processor, a communication interface, a memory, and a communication bus, wherein the processor, the communication interface, and the memory communicate with each other through the communication bus; Memory, used to store computer programs; A processor, when executing a program stored in memory, implements the steps of the method according to any one of claims 1-7.

10. A computer storage medium, characterized in that, The computer storage medium stores a computer program, which, when executed by a processor, implements the steps of any one of the methods described in claims 1-7.

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