A fully distributed satellite power sub-system

Abstract

An embodiment of the present invention discloses a fully distributed satellite power subsystem and a control method; the fully distributed satellite power subsystem includes: a solar panel input conversion device, which is used to provide a power source with a set bus voltage to the power supply bus, and supply the power source with the set bus voltage to the corresponding on-board single machine through the power supply bus; a battery charge and discharge control device, which uses the power source on the power supply bus to charge the corresponding battery pack, and supplies the power source stored in the battery pack to the corresponding on-board single machine through the power supply bus when there is no light; a plurality of power supply modules, which are used to supply the power source output from the solar panel input conversion device or the battery charge and discharge control device to the power supply bus to the corresponding on-board single machine after voltage conversion.

Description

Technical Field

[0001] The embodiments of the present invention relate to the technical field of satellite power control, and in particular, to a fully distributed satellite power subsystem and a control method therefor. Background Art

[0002] Currently, existing satellite power systems generally include solar panels, storage batteries, power controllers, etc. Usually, the power controller includes functions such as solar input control, charging or discharging control of the storage battery, voltage conversion, power distribution, and temperature acquisition. In some satellites, power distribution and thermal control are regarded as independent units. Taking the power controller integrating power distribution and thermal control functions in the above satellite as an example, when the power controller realizes functions such as satellite power input conversion, temperature acquisition, and power distribution control as an independent device, the input voltages of the solar panels and the storage batteries are converted into target voltages required by different on-board units in the power controller, and then are transmitted to the corresponding on-board units through power supply wires. It should be noted that in this power control method, according to the size of the satellite, the length of the power supply wires is usually in the range of dozens of centimeters to several meters. The large line loss caused by the long power supply wires results in different power supply voltages obtained at the on-board unit ends at different distances from the power controller, thus bringing difficulties to the design of the on-board units. In addition, the conversion efficiency of the voltage conversion module in the power controller is different under different load conditions. For the sake of reliability, it is usually designed according to light to medium loads during design, and the working conditions change with the power consumption requirements of the on-board units, resulting in a low power conversion efficiency. On the other hand, the number of power distribution circuits needs to be set in the range of dozens to hundreds according to the satellite requirements, resulting in a large number of cables inside the satellite. The power supply cables and communication cables are intertwined with each other, bringing great difficulties to the assembly and testing of the satellite.

[0003] In addition, the power supply bus voltages of the power sources commonly used in micro-nano satellites are mostly 28V or 42V. Generally, the number of solar cells connected in series in the solar panels is in the range of 20 to 30, and the number of storage batteries connected in series in the storage battery pack is generally 7 or 11 series. Due to the differences in performance of these series-connected solar cells or storage batteries, the output voltages or stored energies will be different during use, and the differences will gradually become larger over time, which will affect the normal operation of the satellite. Summary of the Invention

[0004] In view of this, the embodiments of the present invention are expected to provide a fully distributed satellite power subsystem and a control method therefor; which can optimize the design of the satellite power subsystem, solve the problem that the large number of series-connected solar cells and storage batteries affects the reliability of the whole satellite, and at the same time reduce the great influence of the whole satellite on the design limitations of the components of the power subsystem.

[0005] The technical solution of the embodiments of the present invention is implemented as follows:

[0006] In a first aspect, an embodiment of the present invention provides a fully distributed satellite power subsystem, characterized in that the fully distributed satellite power subsystem includes:

[0007] A solar panel input conversion device, which is used to provide a power supply with a set bus voltage to the power supply bus, and supply the power supply with the set bus voltage to the corresponding on-board single unit through the power supply bus;

[0008] A battery charge and discharge control device, which uses the power on the power supply bus to charge the corresponding battery pack, and supplies power to the corresponding on-board single unit through the power supply bus using the power stored in the battery pack when there is no light;

[0009] Multiple power supply modules, which are used to supply the power output from the solar panel input conversion device or the battery charge and discharge control device to the power supply bus to the corresponding on-board single unit after voltage conversion.

[0010] In a second aspect, an embodiment of the present invention provides a control method for a fully distributed satellite power subsystem, characterized in that the control method can be applied to the fully distributed satellite power subsystem described in the first aspect, and the control method includes:

[0011] When receiving an instruction to power on the entire satellite, each module with the same function reads the default parameters to confirm whether there is a master module;

[0012] When there is no such master module, the modules with the same function negotiate with each other to determine the master module; if there is a master module, proceed to the next step;

[0013] Each module with the same function saves the address of the master module, and each module determines whether to work and the working parameters according to the requirements of the entire satellite, the set working mode and its own priority;

[0014] The modules in the backup state enter the low-power mode, can receive instructions, send their own status, but do not output power externally, and the working modules enter the working mode according to the set parameters;

[0015] For the instructions issued by the on-board computer, all modules can receive them, only the modules in the working mode execute them, and the modules in the backup state receive the instructions, set the corresponding parameters, and do not output power externally;

[0016] All modules send the telemetry and status information reported by the corresponding modules to the master module;

[0017] The master module packs the data of itself and all other modules and sends it to the on-board computer; at the same time, the master module broadcasts a heartbeat packet regularly;

[0018] If all the other modules do not receive the heartbeat packet after the timeout, the backup module enters the working state in the set order and re-negotiates autonomously to determine the master module; if all the other modules receive the heartbeat packet before the timeout, jump to the step: each module of the same function saves the address of the master module, and each module determines whether to work and the working parameters according to the overall satellite requirements, the set working mode and its own priority.

[0019] The embodiment of the present invention provides a fully distributed satellite power subsystem and a control method; for the fully distributed satellite power subsystem provided by the embodiment of the present invention, functional modules are divided according to different functions of the satellite power subsystem, and the power controller in the existing satellite power control system is split into multiple single-function modules. Specifically, the above-mentioned fully distributed satellite power subsystem includes a solar panel input conversion device, a plurality of battery charge and discharge control devices, and a plurality of power supply modules, all of which are independently distributed, optimizing the design of the satellite power subsystem, solving the problem that the large number of series-connected solar cells and battery packs affects the reliability of the whole satellite, and at the same time reducing the influence of the design limitations of the satellite's whole-star on the components of the power subsystem. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a schematic diagram of the composition of the conventional satellite power control system provided by the embodiment of the present invention;

[0021] Figure 2 It is a schematic diagram of the composition of a fully distributed satellite power subsystem provided by the embodiment of the present invention;

[0022] Figure 3 It is a schematic diagram of the control method flow of a fully distributed satellite power subsystem provided by the embodiment of the present invention. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0023] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention.

[0024] See Figure 1 , which shows the composition of the conventional satellite power control system 1A. As Figure 1 shown, the satellite power control system 1A includes: a plurality of solar panels 101, a plurality of battery packs 102, and a power controller 103; among them,

[0025] In the power controller 103, a solar input control module 1031 (MPPT (Maximum Power Point Tracking) controller, or shunt controller) corresponding to the solar panel 101 is provided, as well as a battery charge and discharge control module 1032, a voltage conversion module 1033, a power distribution switch 1034, and a thermal control switch 1035 corresponding to the battery pack 102. It should be noted that the solar input control module 1031 can be selected according to actual design requirements.

[0026] It should be noted that in Figure 1 only shows that the satellite power control system 1A includes 2 solar panels 101 and corresponding 2 solar input control modules 1031, as well as 2 battery packs 102 and corresponding 2 battery charge and discharge control modules 1032. In the specific implementation process, the specific quantity of the above components is subject to the specific actual power demand situation, and no specific limitation is made in the embodiments of the present invention.

[0027] It can be understood that in Figure 1 shown satellite power control system 1A, the power provided by the solar panel 101 and the battery pack 102 are respectively transmitted to the corresponding solar input control module 1031 and battery charge and discharge control module 1032 in the power controller 103, and after being controlled by the solar input control module 1031 and the battery charge and discharge control module 1032, they are transmitted to the voltage conversion module 1033 through the power supply bus. It can be understood that a bus voltage output unit 10331 can be provided in the voltage conversion module 1033, so that the power will be supplied to the corresponding on-board unit 104 or the thermal control device 105 in the corresponding on-board unit 104 through the power distribution switch 1034 or the thermal control switch 1035 by using the bus voltage output unit 10331; of course, a voltage conversion unit 10332 will also be provided in the voltage conversion module 1033, so that the power will be voltage-converted by using the voltage conversion unit 10332 and then supplied to the corresponding on-board unit 104 through the power distribution switch 1034. It should be noted that the voltage conversion unit 10332 may be a 5V power conversion unit or a 12V voltage conversion unit.

[0028] Of course, in the existing satellite power control system 1A, a power lower computer 106 is also provided, which is electrically connected to the on-board computer 107 through a communication bus and is used for the on-board computer 107 to remotely control and remotely measure the power supply state or temperature state of the satellite power control system 1A. In addition, a data acquisition module 108 is usually provided in the satellite power control system 1A to collect relevant analog data, such as temperature.

[0029] By Figure 1It can be seen that in the existing satellite power control system 1A, the power controller 103 needs to set the bus voltage output unit 10331 or multiple different types of voltage conversion units 10332 according to the load condition, and needs to set more distribution switches 1034 or thermal control switches 1035 according to the requirements of the on-board unit 104, resulting in a large number of cables inside the satellite, and the power supply wires and communication wires are intertwined with each other, bringing great difficulties to the assembly and testing of the satellite.

[0030] On the other hand, in the specific implementation process, the solar panel 101 is usually composed of multiple solar cells connected in series, and the battery pack 102 is usually composed of multiple batteries connected in series. If one of the solar cells in a series of solar cells fails, it will affect the output power of the entire series of solar cells; similarly, if one of the batteries in a series of batteries has a problem, it will cause the capacity of the entire battery pack to decrease, thereby affecting the reliability of the satellite. In addition, when considering the structure factors in the series-parallel design of the solar panel 101 and the battery pack 102, it will result in a relatively small proportion of the effective area of the solar panel 101 in the total area. The installation position, weight, and external dimensions of the battery pack 102 need to consider factors such as the center of mass of the entire satellite and space, which impose greater restrictions on the components of the satellite power subsystem.

[0031] Based on the above description, refer to Figure 2 , which shows the composition of a fully distributed satellite power subsystem 2 provided by an embodiment of the present invention. The fully distributed satellite power subsystem 2 includes:

[0032] A solar panel input conversion device 10, which is used to provide a power supply with a set bus voltage to the power supply bus 20, and supply the power supply with the set bus voltage to the corresponding on-board unit 104 through the power supply bus 20;

[0033] A battery charge and discharge control device 30, which uses the power supply on the power supply bus 20 to charge the corresponding battery pack 102, and supplies power to the corresponding on-board unit 104 through the power supply bus 20 using the power stored in the battery pack 102 when there is no light;

[0034] Multiple power supply modules 40, which are used to supply the power output from the solar panel input conversion device 10 or the battery charge and discharge control device 30 to the power supply bus 20 to the corresponding on-board unit 104 after voltage conversion.

[0035] For Figure 2The described fully distributed satellite power sub-system 2 divides functional modules according to the different functions of the satellite power sub-system, and splits the power controller 103 in the existing satellite power control system 1A into multiple single-functional modules. Specifically, the fully distributed satellite power sub-system 2 includes a solar panel input conversion device 10, a battery charge and discharge control device 30, and multiple power supply modules 40, all of which are independently and distributively arranged, optimizing the design of the satellite power sub-system, solving the problem that the large number of series-connected solar cells and battery packs affects the reliability of the entire satellite, and at the same time reducing the limitation of the satellite's entire satellite on the design of the power sub-system components.

[0036] For Figure 2 In some possible implementation manners of the described fully distributed satellite power sub-system 2, the solar panel input conversion device 10 includes multiple micro-solar modules 11, and each of the micro-solar modules 11 includes: a solar panel 101 and a solar input control module 1031; wherein, the solar input control module 1031 is connected to the corresponding power supply module 40 through the power supply bus 20; and, the solar input control module 1031 realizes interactive communication with the on-board computer 107 through the communication bus 50.

[0037] It should be noted that in the specific implementation process, the solar input control module 1031 can be designed on the solar panel 101 or inside the satellite body. To reduce cable loss, the preferred way is to design the solar input control module 1031 on the solar panel, as close as possible to the solar panel 101. In addition, the solar panel 101 can be designed with several series-parallel combinations of solar cells according to actual needs, and the number of its series connections can be designed according to actual needs, generally less than the number of series-connected solar cells in existing satellites, and the minimum can be 1 or 2.

[0038] For possible implementation manners, in some examples, the solar input control module 1031 uses a boost method to raise the power voltage generated by the corresponding solar panel 101 to the set bus voltage. It can be understood that when the bus voltage corresponding to the power supply bus 20 is relatively high, at the same power, the required current is small, which can reduce line loss and improve voltage conversion efficiency.

[0039] In addition, it should be noted that in the specific implementation process, multiple micro solar modules 11 jointly share the power of the entire satellite. When additional power or redundancy is required, only the number of micro solar modules 11 needs to be increased, which is simple and reliable to operate. On the other hand, different micro solar modules 11 can automatically interact and communicate through the communication bus 50 to set the working mode. For example, the X + y cold standby / hot standby mode (X micro solar modules 11 provide the power required by the entire satellite, and y micro solar modules 11 are in the cold standby / hot standby state), the current sharing mode, etc. Of course, different micro solar modules 11 can also set the working mode through the on-board computer 107.

[0040] For Figure 2 For the fully distributed satellite power subsystem 2 shown, in some possible implementation manners, the battery charge and discharge control device 30 includes a plurality of micro battery modules 31, and each of the micro battery modules 31 includes: a battery pack 102 and a battery charge and discharge control module 1032; wherein, the battery charge and discharge control module 1032 is connected to the corresponding power supply module 40 through the power supply bus 20; and, the battery charge and discharge control module 1032 realizes interactive communication with the on-board computer 107 through the communication bus 50.

[0041] It should be noted that in the embodiment of the present invention, the battery charge and discharge control module 1032 and the corresponding battery pack 102 form a micro battery module 21. The battery charge and discharge control module 1032 uses the electric energy of the power supply bus 20 to charge the battery, and converts the electric energy stored in the battery pack 102 into the bus voltage when there is no light, and supplies power to the on-board single machine 104 after voltage conversion by the power supply module 40. The number of batteries connected in series in the battery pack 102 can be designed according to needs, and the minimum can be a single cell or 2 cells connected in series. In the specific implementation process, multiple micro battery modules 21 jointly supply power to the entire satellite.

[0042] For possible implementation manners, in some examples, in the charging mode, the battery charge and discharge control module 1032 step-down converts the set bus voltage on the power supply bus 20 into the charging voltage of the battery pack 102 to charge the battery pack 102; in the discharging mode, the battery charge and discharge control module 1032 boosts the voltage of the battery pack 102 to the set bus voltage and supplies it to the power supply bus 20, and then transmits it to the corresponding power supply module 40 through the power supply bus 20. It can be understood that when the bus voltage corresponding to the power supply bus 20 is relatively high, at the same power, the required current is small, which can reduce the line loss and improve the voltage conversion efficiency.

[0043] In addition, different micro-battery modules 31 can set their own working modes and parameters according to parameters such as their own battery power, battery life, charge and discharge current, etc., such as charging, discharging or standby. Similarly, different micro-battery modules 31 can automatically communicate with each other through the communication bus 50 to set the working mode, or can also set the working mode through the on-board computer 107.

[0044] It should be noted that in the embodiment of the present invention, the solar panel input conversion device 10 and the battery charge and discharge control device 30 can be installed at different positions of the satellite.

[0045] For Figure 2 For the fully distributed satellite power sub-system 2 shown, in some possible implementation manners, each of the power supply modules 40 includes a voltage conversion module 1033, a power distribution switch 1034 and a power supply control unit 41; wherein, the power supply control unit 41 is used to control the voltage conversion module 1033 to convert the set bus voltage of the power supply bus 20 into a target voltage supplied to the on-board single machine 104.

[0046] For the above implementation manner, in some examples, the power supply control unit 41 is further used to control the opening or closing of the power distribution switch 1034, so that when the power distribution switch 1034 is closed, the power converted by the voltage conversion module 1033 can be transmitted to the corresponding on-board single machine 104.

[0047] It should be noted that the power supply and distribution module 40 steps down the higher bus voltage on the power supply bus 20 to the target voltage required by the on-board single machine 104 to supply power to the on-board single machine 104. If the on-board single machine 104 can directly use the above set bus voltage, in the specific implementation process, the power supply control unit 41 can Figure 2 The voltage conversion module 1033 in is switched to the bus voltage output unit 10331 to output the voltage on the power supply bus 20 without conversion to the corresponding on-board single machine 104, that is to say, the power supply and distribution module 40 only plays the role of short-circuit protection and power switch, and does not regulate the voltage; or, according to the voltage requirement of the on-board single machine 104, the power supply control unit 41 Figure 2 The voltage conversion module 1033 in is switched to the voltage conversion unit 10332 to convert the voltage on the power supply bus 20 into a set voltage and then output it to the corresponding on-board single machine 104, for example, the converted voltage is 5V or 12V. In addition, if the on-board single machine has high requirements for power supply, multiple power supply and distribution modules 40 can also supply power to one on-board single machine 104, and multiple power supply modules 40 jointly provide the current required by the on-board single machine 104, or the X+y cold standby / hot standby working mode.

[0048] For Figure 2The fully distributed satellite power subsystem 2 shown, in some possible implementation manners, such as Figure 2 as described, the fully distributed satellite power subsystem 2 further includes a plurality of thermal control modules 60, and each thermal control module 60 includes: a thermal control unit 601, a thermistor 602, and a heating tape 603; wherein,

[0049] the thermal control unit 601 is electrically connected to the communication bus 50 to receive the temperature control range of the corresponding on-board unit 104 based on the communication bus 50; and, collect the temperature value of the corresponding on-board unit 104 through the thermistor 602; and, when the temperature value of the on-board unit 104 is not within the temperature control range, control the switch state of the heating tape 603.

[0050] It should be noted that the thermal control module 60 collects the temperature of the on-board unit 104 to control the switch of the heating tape 603 according to the actual temperature and temperature requirement of the on-board unit 104. One or more thermistors 602 and heating tapes 603 can be provided according to actual needs, and they can also exist in one thermal control module 60 at the same time, or there can be only the heating tape 603 or the thermistor 602. Of course, in the specific implementation process, a plurality of thermal control modules 60 can control the temperature of one on-board unit 104 at the same time. Of course, in the specific implementation process, the thermal control module 60 can also be installed according to the actual needs of the on-board unit 104.

[0051] For Figure 2 the fully distributed satellite power subsystem 2 shown, in some possible implementation manners, each micro solar module 11, each micro battery module 31, each power supply module 40, and each thermal control module 60 correspond to a communication address to communicate with each other through the communication bus and receive the instructions issued by the on-board computer 107 through the communication bus.

[0052] It can be understood that in the fully distributed satellite power subsystem 2, all functional modules have a unique communication address to communicate with each other through the communication bus 50, and can send status telemetry information to the on-board computer 107 through the communication bus 50, and at the same time receive the instructions of the on-board computer 107.

[0053] In Figure 2In the fully distributed satellite power sub-system 2 shown, a smaller number of solar cells and battery packs respectively form the smallest functional modules, avoiding the situation of string failure caused by the damage of a single battery or solar cell in the battery pack 102 or the solar panel 101; at the same time, the impact on the power system caused by the performance differences of different solar cells or battery monomers is reduced. In the specific implementation process, multiple micro-solar modules 11 or multiple micro-battery modules 31 jointly provide the power required for the entire satellite, reducing the requirements for each functional module, improving the reliability of the power system, and facilitating power expansion. In addition, the boost-type solar input control module 1031 and the buck-boost battery charge and discharge control module 1032 can provide a higher bus voltage to the power supply bus 20 to reduce the power loss on the cable; on the other hand, in the embodiment of the present invention, the battery, power distribution, and thermal control are separately divided into multiple small modules, reducing the requirements for the internal space of the satellite body, making full use of the space, and reducing the difficulty of structural design; finally, in the embodiment of the present invention, the connection method of the power supply bus 20 and the communication bus 50 is adopted, and each functional module is installed near the corresponding on-board single machine nearby, reducing the number of cables in the satellite and the complexity of cable connection.

[0054] In view of the large number of functional modules in the fully distributed satellite power sub-system 2, if the on-board computer 107 communicates with all functional modules respectively, the requirements for the on-board computer are relatively high. Therefore, as Figure 3 shown, the interactive communication between each functional module and the on-board computer 107 can be carried out in the following manner:

[0055] S301. When receiving the instruction to power on the entire satellite, each module with the same function reads the default parameters to confirm whether there is a main module;

[0056] S302. When there is no such main module, the modules with the same function negotiate with each other to determine the main module; if there is such main module, go to step S303;

[0057] S303. Each module with the same function saves the address of the main module, and each module determines whether to work and the working parameters according to the requirements of the entire satellite, the set working mode and its own priority; it should be noted that the own priority of each module can be set according to the instruction or determined according to the address of each module, etc.;

[0058] S304. The modules in the backup state enter the low-power mode, can receive instructions, send their own status, but do not output power externally, and the working modules enter the working mode according to the set parameters;

[0059] S305. For the instructions sent by the on-board computer, all modules can receive them. Only the modules in the working mode will execute the instructions. The modules in the backup state receive the instructions, set the corresponding parameters, and do not output power externally.

[0060] S306. All modules send the telemetry and status information reported by the corresponding modules to the main module.

[0061] S307. The main module packs the data of itself and all other modules and sends it to the on-board computer. At the same time, the main module broadcasts a heartbeat packet regularly.

[0062] S308. If all other modules still do not receive the heartbeat packet after timeout, the backup module enters the working state in the set order and re-negotiates autonomously to determine the main module. If all other modules receive the heartbeat packet before timeout, jump to step S303.

[0063] For the micro solar module 11 or the micro battery module 31, the number of modules in the working state can be set to be greater than the actual required number of modules to ensure the continuity of work after the main module times out. For the on-board single machine 104 that needs to work continuously, one or more modules of its power supply module 40 can be set to be in the hot standby state all the time to ensure the continuity of work.

[0064] It should be noted that: among the technical solutions recorded in the embodiments of the present invention, they can be combined arbitrarily without conflict.

[0065] As mentioned above, this is only the specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention can easily think of changes or substitutions, which should all be covered within the protection scope of the present invention. Therefore, the protection scope of the present invention should be subject to the protection scope of the claims.

Claims

1. A fully distributed satellite power subsystem, characterized in that The fully distributed satellite power subsystem includes: A solar panel input conversion device, which is used to provide power with a set bus voltage to the power supply bus and supply the power with the set bus voltage to the corresponding on-board unit through the power supply bus; wherein, the solar panel input conversion device includes a plurality of micro solar modules; A battery charge and discharge control device, which uses the power on the power supply bus to charge the corresponding battery pack and supplies power to the corresponding on-board unit through the power supply bus using the power stored in the battery pack in the absence of light; wherein, the battery charge and discharge control device includes a plurality of micro battery modules; A plurality of power supply modules, which are used to supply the power output to the power supply bus by the solar panel input conversion device or the battery charge and discharge control device to the corresponding on-board unit after voltage conversion; Wherein, the fully distributed satellite power subsystem further includes a plurality of thermal control modules; Wherein, each of the micro solar modules, each of the micro battery modules, each of the power supply modules, and each of the thermal control modules corresponds to a communication address to communicate with each other through a communication bus and receive instructions sent by the on-board computer through the communication bus; Wherein, when receiving the instructions sent by the on-board computer, the main module packs the data of itself and the other modules and sends it to the on-board computer; at the same time, the main module broadcasts a heartbeat packet regularly; if the other modules still do not receive the heartbeat packet after timeout, the backup module enters the working state in accordance with the set order and re-autonomously negotiates to determine the main module; if the other modules receive the heartbeat packet before timeout, jump to the step: each module with the same function saves the address of the main module, and each module determines whether to work and the working parameters according to the requirements of the whole satellite, the set working mode, and its own priority; Wherein, each module with the same function reads the default parameters to confirm whether there is a main module; when there is no main module, the modules with the same function negotiate with each other to determine the main module.

2. The fully distributed satellite power sub-system according to claim 1, wherein Each of the micro solar modules includes: a solar panel and a solar input control module; wherein, the solar input control module is connected to the corresponding power supply module through the power supply bus; and, the solar input control module realizes interactive communication with the on-board computer through the communication bus.

3. The fully distributed satellite power subsystem according to claim 2, characterized in that, The solar input control module uses a boost method to increase the power voltage generated by the corresponding solar panel to the set bus voltage.

4. The fully distributed satellite power sub-system according to claim 1, characterized in that, Each of the micro battery modules includes: a battery pack and a battery charge and discharge control module; wherein, the battery charge and discharge control module is connected to the corresponding power supply module through the power supply bus; and, the battery charge and discharge control module realizes interactive communication with the on-board computer through the communication bus.

5. The fully distributed satellite power sub-system according to claim 4, characterized in that, In the charging mode, the battery charge and discharge control module steps down the set bus voltage on the power supply bus to the charging voltage of the battery pack to charge the battery pack; in the discharging mode, the battery charge and discharge control module steps up the voltage of the battery pack to the set bus voltage and supplies it to the power supply bus, and then transmits it to the corresponding power supply module through the power supply bus.

6. The fully distributed satellite power sub-system according to claim 1, wherein Each of the power supply modules includes a voltage conversion module, a power distribution switch, and a power supply control unit; wherein, the power supply control unit is used to control the voltage conversion module to convert the set bus voltage of the power supply bus into a target voltage supplied to the on-board single unit.

7. The fully distributed satellite power sub-system according to claim 6, characterized in that The power supply control unit is further used to control the opening or closing of the power distribution switch, so that when the power distribution switch is closed, the power converted by the voltage conversion module can be transmitted to the corresponding on-board single unit.

8. The fully distributed satellite power sub-system according to claim 1, wherein, Each of the thermal control modules includes: a thermal control unit, a thermistor, and a heating tape; wherein, The thermal control unit is electrically connected to the communication bus to receive the temperature control range of the corresponding on-board single unit based on the communication bus; and, collect the temperature value of the corresponding on-board single unit through the thermistor; and, when the temperature value of the on-board single unit is not within the temperature control range, control the switch state of the heating tape.

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