CN215733484U - Satellite solar power module - Google Patents

Abstract

A satellite solar power module comprising: the solar battery pack is electrically connected with electric equipment on the satellite to form a bus and used for receiving sunlight, performing photoelectric conversion on the sunlight and then supplying electric power to the electric equipment, the control management module is electrically connected to the bus in a mode of acquiring output voltage and output current of the solar battery pack to generate an optimal MPPT control instruction and regulating and controlling output power of the solar battery pack according to the instruction, the control management module is arranged in the mounting box, and at least one shielding layer which is used for shielding external electromagnetic interference and wraps the control management module is arranged in the mounting box.

Description

Satellite solar power module

Technical Field

The utility model relates to a power supply module used for a satellite, in particular to a solar power supply module for the satellite.

Background

At present, satellite technology becomes a development direction of aerospace technology in various countries, wherein micro satellites are widely concerned by people due to the characteristics of small size, light weight, low cost and the like. The design and development period of the micro satellite is short, the micro satellite is convenient for modularization and batch production, and the advantages which are not possessed by other satellites are widely adopted.

With the development of commercial aerospace, more stringent requirements are put on commercial satellites, and the core requirements of the commercial satellites are as follows: the development cost is low, the development period is short, namely the business mode of commercial aerospace determines that the satellite needs to be shifted from single customization to productization, serialization and shelving, and therefore the design and development of the commercial satellite are required to have good adaptability and expandability. The satellite energy system is used as a large component of the satellite system, the requirements are the same, the adaptability is wide, and the expandability is strong, so that the satellite energy system is one of important design ideas of commercial satellite energy systems.

The power supply system of the satellite is one of several core systems of the satellite, is used for providing power for the whole satellite, and is the life line of the satellite. For a low orbit microsatellite, a power supply system must have the characteristics of high reliability, small volume, light weight, high efficiency and the like.

CN107579587A discloses an energy system suitable for LEO satellite and its control method, which comprises a solar cell array, a PPT circuit unit, a storage battery, a capacitor array, a satellite platform load and a remote measurement and control unit; the MPPT circuit unit performs peak power tracking on the solar cell array in a triple redundancy hot backup mode by adopting three DC-DC conversion modules connected in parallel, closed-loop control is performed on the MPPT circuit unit by adopting a majority voting control circuit, and each control circuit generates a driving signal to perform closed-loop control on the MPPT circuit corresponding to the control circuit according to an output voltage signal and an output current signal of the solar cell array module and a voltage signal and a current signal of a storage battery pack so as to realize maximum power tracking on the solar cell array module and charge management on the storage battery pack.

The utility model discloses an utilize the MPPT algorithm to carry out output optimization and manage to storage battery charging to solar array, but the control that its control circuit relates to, decision-making module is more makes MPPT become a comparatively accurate electronic components or electronic module, it receives external electromagnetic radiation influence in complicated electromagnetic environment and cosmic radiation in the space very easily, do not consider the electromagnetic shield protection to the MPPT module among this prior art, probably can cause the problem that control module received the electromagnetic interference inefficacy.

SUMMERY OF THE UTILITY MODEL

To solve at least some of the problems in the prior art, the present invention provides a satellite solar power module, including: the solar battery pack is electrically connected with electric equipment on the satellite to form a bus and used for receiving sunlight, performing photoelectric conversion on the sunlight and then supplying electric power to the electric equipment, the control management module is electrically connected to the bus in a mode of acquiring output voltage and output current of the solar battery pack to generate an optimal MPPT control instruction and regulating and controlling output power of the solar battery pack according to the instruction, the control management module is arranged in the mounting box, and at least one shielding layer which is used for shielding external electromagnetic interference and wraps the control management module is arranged in the mounting box.

Preferably, the mounting box is provided with a plurality of circuit sockets according to the connection requirements of the control management module, wherein the circuit sockets at least comprise a solar battery pack cathode socket, a solar battery pack anode socket, a bus anode socket, a storage battery pack cathode socket and an electric equipment cathode socket.

Preferably, the mounting box is internally provided with a mounting table matched with the bottom appearance of the control management module, the mounting table is at least provided with a concave part which is concave inwards according to the bottom appearance of the circuit board of the control management module, and meanwhile, the periphery of the mounting table is provided with assembling holes for fixing the control management module.

Preferably, at least one flange protruding outwards is arranged on the periphery of the mounting table, a plurality of positioning holes are formed on the periphery of the mounting box in a mode of matching the shape of the flange, and the mounting table is connected to the mounting box through the shape matching mode of the flange and the positioning holes.

Preferably, when the electric energy required by the electric equipment is smaller than that of the solar battery pack, the solar battery pack can be electrically connected to the storage battery pack to form a charging loop, and the control management module comprises an IC chip, wherein the IC chip is electrically connected with the power output end of the solar battery pack.

Preferably, the control management module is composed of at least 2 IC chips, and different IC chips and their associated circuits are arranged independently.

Preferably, the IC chip is electrically connected to a power input terminal of the secondary battery pack.

Preferably, a DC-DC converter is disposed between lines electrically connected to the solar cell set by the control management module.

Preferably, the IC chip further integrates an SOC detection unit electrically connected to the secondary battery pack.

Preferably, the control management module further comprises a control loop, the control loop is electrically connected to the IC chip, the solar battery pack and the storage battery pack, respectively, wherein the DC-DC converter is disposed in the control loop.

The utility model has the following beneficial technical effects:

through install the mounting box additional to control management module skin and set up the shielding layer of one deck electromagnetic radiation prevention inside the mounting box and to the electronic components on the control management module including setting up both played physical protection function and played the electromagnetic protection function, have very big benefit to the functional integrality of the IC chip of protection control management module under the space environment that electromagnetic environment is complicated changeable.

Drawings

FIG. 1 is a schematic diagram of the overall circuit connection of the present invention;

FIG. 2 is a schematic circuit diagram of a control management module according to the present invention;

FIG. 3 is a schematic view of a partial half-section structure of the mounting box of the present invention;

FIG. 4 is a schematic view of the structure of the mounting table of the present invention;

in the figure: 100. a solar cell array; 200. a control management module; 210. an IC chip; 211. an SOC detection unit, 220, a control loop; 300. a battery pack; 400. an electricity-consuming device; 500. mounting a box; 510. an installation table; 520. a shielding layer; 530. and a circuit socket.

Detailed Description

The following detailed description is made with reference to the accompanying drawings.

Fig. 1 shows a satellite solar power module, and since the present invention is used for satellites in space, the present invention at least includes a solar cell set 100 for acquiring solar energy in space as a main energy source of the satellites. The solar cell array 100 is formed by combining a plurality of solar cells arranged in a certain arrangement manner.

Each solar cell has a sheet-like or plate-like structure, and the solar cell is made of a novel composite material selected from various materials such as gallium arsenide triple junction (GaInP) for obtaining a certain photoelectric conversion efficiency₂GaAs/Ge) material, copper indium selenide (CuInSe)₂) Material, Copper Indium Gallium Selenide (CIGS) material, TiO₂The nano-crystalline material and the single-crystal silicon material made of the same material have different photoelectric conversion efficiencies, for example, the photoelectric conversion efficiency of the triple-junction gallium arsenide is over 28%, while the photoelectric conversion efficiency of the single-crystal silicon material is only about 12-14%, but the triple-junction gallium arsenide has higher cost due to complex manufacturing process. Therefore, the material of the solar cell set 100 is selected according to the use requirement of the satellite, the working environment, the manufacturing budget, and other factors.

The solar array 100 may be configured as a low voltage battery array, so that the satellite, when applied to an area with strong illumination variation, can still maintain high overall output power if part of the solar cells are shielded. Preferably, the solar cell set 100 can be adaptively changed and arranged according to specific use conditions or use environments of the satellite, for example, for different types of satellites such as a small satellite with low orbit, a satellite with high power using equipment 400, a satellite operating in an orbit with uniform light irradiation, and the like, so as to adapt to the different use conditions of the satellite.

Since the satellite moves in space in a long-term, orbiting motion about a fixed primary star (e.g., the earth), the satellite will be in the sun's shadow for a period of time, referred to as the shadow period. It is apparent that the solar cell set 100 cannot or can receive only little light during the shadow period, and thus the solar cell set 100 cannot perform power supply or photoelectric conversion operation during the shadow period. A period of time excluding the shadow period in the full period of the satellite moving around the main satellite is referred to as an illumination period, and at this time, the solar cell set 100 may collect sunlight at the maximum power to perform photoelectric conversion to generate electric energy by adjusting the attitude of the satellite.

In order to ensure that the satellite can be normally powered on to maintain the movement and attitude adjustment of the satellite or the continuous and stable operation of the power utilization functional equipment on the satellite in the period from the movement to the shadow period, the storage battery pack 300 is further arranged in the satellite power supply module provided by the utility model. The battery pack 300 is electrically connected with the solar battery pack 100 to realize the power intercommunication between the battery pack 300 and the solar battery pack 100, and the satellite can selectively turn on the battery pack 300 to supply power to the electric equipment 400 on the whole satellite in the case that the satellite enters a shadow period. For the purpose of charging the battery pack 300, the solar cell pack 100 performs a charging operation for the battery pack 300 through its electrical connection with the battery pack 300 during the light period to receive light and generate electricity.

In order to adapt to the harsh environment in outer space and the reduced requirements of the overall weight and volume of the satellite, the material of the battery pack 300 is generally selected from the types with higher energy density, such as lithium ion batteries, nickel-chromium batteries, nickel-hydrogen batteries, and the like. Although the lithium ion storage battery has high energy density and good charge and discharge performance, the discharge cut-off voltage of the lithium ion storage battery is about 2.7V, the charge termination voltage is about 4.2V, and the average discharge voltage is about 3.5V, compared with the average discharge voltage of a nickel-metal hydride storage battery and a cadmium-nickel storage battery which is about 1.25V, the number of lithium battery packs is only one third of the number of nickel-metal hydride batteries and cadmium-nickel batteries, and the cost is greatly reduced. However, the lithium ion batteries also have the risk of explosion of the batteries due to overcharge and overdischarge, and for a satellite running for a long time, voltage difference is formed between each lithium ion battery and other single lithium ion batteries in the battery pack 300 in a long-term charge-discharge cycle, so that the risk of overcharge and overdischarge of the single lithium ion batteries is possibly increased in the unified charging or discharging operation of the battery pack 300. However, for a small satellite running in a low orbit, the lithium ion storage battery can be adopted on the small satellite running in the low orbit to reduce the volume and the weight of the satellite due to small volume, single function, shallow discharge depth of the storage battery and low requirement on the whole service life of the satellite.

The device requiring power provided on the satellite is essentially a load, and the load needs to be supplied with power continuously in a normal condition to ensure its normal operation, so that the solar cell set 100 and the battery set 300 are electrically connected to the power-consuming device 400. Preferably, during the time period when the satellite is in the illumination period, the solar cell set 100 receives sunlight to perform photoelectric conversion to generate electric power, and then divides the electric power into at least two parts, one part is used for charging the storage battery, and the other part is directly supplied to the electric device 400 to maintain the normal operation of the electric device. During the shadow period, the battery pack 300 supplies power to the electric device 400. And the lines of the solar cell set 100 supplying power to the battery pack 300 and the electric device 400 are called bus bars.

In order to ensure that the electric equipment 400 has stable power supply under any condition, a certain design is made on power supply strategies of the solar battery pack 100 and the storage battery pack 300 in an illumination period and a shadow period, during the illumination period, the power generated by the solar battery pack 100 is preferentially supplied to the electric equipment 400 for use, when the output power of the solar battery pack 100 is greater than the actual load demand of the electric equipment 400, the redundant power is charged into the storage battery pack 300 for storage, and when the power generated by the solar battery pack 100 is insufficient to supply other use demands of the electric equipment, the storage battery pack 300 assists in supplying power to the electric equipment 400 so as to ensure the power demand of the electric equipment 400. Meanwhile, in order to minimize the overcharge and overdischarge of the single cells in the battery pack 300, it is necessary to perform more precise control and management on the charging and discharging processes of the battery pack 300.

In order to realize the functions of controlling the solar cell set 100 and the storage battery set 300 to supply power to the electric equipment 400 and manage charging and discharging of the storage battery set 300 according to the above power supply strategy during the light period and the shadow period, the power module provided by the present invention is further provided with a control management module 200 (shown in fig. 2), the control management module 200 is composed of at least two special IC chips 210 with MPPT function and their supporting circuits, two of the special IC chips 210 having MPPT function are identical in at least function, so that there are two complete sets of IC chips 210 for control management purposes in the entire control management module 200, the integrated control IC chip 210 is used for forming mutual insurance by using two sets of same control IC chips 210 in a severe and complicated space environment, and the condition that the whole satellite electric equipment 400 cannot be normally powered on for use or the power supply is overloaded after one IC chip 210 is damaged is prevented. Preferably, a status check circuit is disposed in the control management module 200, and the status check circuit is electrically connected to all the IC chips 210, and detects whether one of the IC chips 210 is operating normally, and if it is detected that the IC chip 210 has no signal flowing out, cannot operate, and the like, it is determined that the IC chip 210 is damaged, and at this time, the status check circuit selects to start another backup IC chip 210 to operate.

The IC chip 210 has integrated thereon functions for managing the output power of the solar cell module 100, including functions for detecting the output current and the output voltage of the solar cell module 100. The IC chip 210 is electrically connected to the solar cell module 100, so that the IC chip 210 can detect the output current and the output voltage of the solar cell module 100 in real time and utilize the detected related data to the next MPPT calculation step.

The IC chip 210 performs decision calculation on the output current and the output voltage collected from the solar cell set 100 by using the MPPT algorithm built therein to form at least one optimum MPPT control command for controlling the output efficiency of the solar cell set 100. The MPPT algorithm can adopt a relatively mature disturbance observation method in the industry, the working principle is that the output power of the current solar battery pack 100 is measured, then a small voltage component disturbance is added to the original output voltage, the output power can be changed, the power after the change is measured, and the change direction of the power can be obtained by comparing the power before the change with the power before the change. If the power is increased, the original disturbance is continuously used, and if the power is reduced, the disturbance direction is changed. The MPPT chip cannot calculate the optimum MPPT control command once at this time, but needs to form the optimum MPPT control command through the varied power feedback after at least one small perturbation is performed.

The IC chip 210 also integrates a function for managing the charging of the battery pack 300, and the function also includes detecting a voltage signal and a current signal of the battery pack 300. The IC chip 210 is electrically connected to the battery pack 300, so that the IC chip 210 can detect a current signal and a voltage signal of the battery pack 300 in real time and utilize the detected related data to the subsequent formation of a charge control command. The current signal and the voltage signal may be current and voltage values of the charging of the battery pack 300.

The IC chip 210 can perform decision calculation on the current signal and the voltage signal collected from the battery pack 300 by using a charging control strategy program built therein to form at least one optimal charging control command for controlling charging of the battery pack 300. The storage battery pack 300 can work under proper charging power or voltage, and the problem of service life reduction of the storage battery pack 300 caused by over-charging and over-discharging of the storage battery pack 300 is effectively solved.

In order to implement the above-mentioned optimal MPPT control command and optimal charging control command, the control management module 200 further includes a control loop 220, and the control loop 220 is electrically connected to the IC chip 210, and simultaneously electrically connected to the solar battery pack 100 and the storage battery pack 300, so that the control loop 220 can control the output efficiency of the solar battery pack 100 and/or the charging mode of the storage battery pack 300 according to the optimal MPPT control command and the optimal charging control command received from the IC chip 210. The control method can be realized by the combined action of several DC-DC converters arranged in the control loop 220, and the DC-DC converters can adjust the related power output and charging voltage in a voltage boosting and reducing manner to realize charging modes such as constant current charging and constant power charging.

Preferably, the control circuit 220 is implemented with an IC chip to achieve higher integration and refinement.

The MPPT function of the IC chip 210 is a maximum power point tracking technique, which can monitor the discharge voltage of the solar cell array 100 in real time and track the maximum voltage and current values, so that the solar cell array 100 can keep charging the storage battery 300 with the maximum power, thereby improving the effective utilization rate of the power generated by the solar cell array 100. In some embodiments, the overall output efficiency of the solar cell array 100 can be increased to over 90% by removing the transmission loss, which greatly increases the working efficiency of the power module provided by the present invention.

In addition, an SOC detection unit 211 is integrated on the IC chip 210, and the SOC detection unit 211 is electrically connected to the battery pack 300 and used for calculating the remaining capacity of the battery according to the detected charge-discharge voltage of the battery pack 300 by means of numerical fitting or the like. In some embodiments, the calculated remaining power may also be used to adjust the load intensity of the power-consuming equipment 400 located on the satellite in real time, so that in the case that the power photoelectrically converted by the solar battery 100 is insufficient for the power-consuming equipment 400 to be used and the remaining power of the battery pack 300 is low, the power-consuming equipment 400 is properly controlled to reduce the power-consuming load through its electrical connection with the control circuit 220, so as to meet the minimum working requirement of the satellite.

The IC chip 210 can be fabricated into chip-scale devices, thereby greatly simplifying external devices and improving the integration level, so that the volume of the power module provided by the utility model can be further reduced. Meanwhile, the IC chip 210 has a relatively wide application range, and input requirements of various solar cell sets 100 and input requirements of various storage battery packs 300 can be met by simply adjusting matching parameters of peripheral circuits of the IC chip, so that relatively high universality and expansibility are achieved.

In addition, the IC chip 210 can also control the input voltage of the solar battery pack 100 flowing to the storage battery pack 300, so that the storage battery pack 300 can be charged and discharged according to a suitable current/voltage sharing or fixed power, the overcharge and overdischarge conditions of the storage battery pack 300 are reduced, and the service life of the storage battery pack 300 is prolonged.

Preferably, the control and management module can be disposed in a smaller mounting box 500 (as shown in fig. 3), the box size depends on the size of the selected volume of the electronic component parts in the control and management module, and in general, the chip-level control and management module with MPPT control function, which has a simpler function, is smaller in volume, so that the mounting box 500 can be made smaller in volume accordingly. The smaller mounting box 500 is particularly suitable for the installation work on the current hot micro-satellite, and because it needs to cooperate with the solar battery to perform the work of regulating and controlling the corresponding output characteristics, it is generally recommended to install the mounting box 500 in the area close to the negative electrode of the solar battery panel sailboard on the satellite. In order to facilitate the connection of the mounting box 500 to the satellite housing or the satellite mounting frame, at least one mounting hole protruding outwards is formed in the outer side surface of the mounting box 500, and the aperture of the mounting hole is set to be the diameter of a universal screw, so that an engineer can conveniently fix the mounting box 500 at the position by penetrating the universal screw into the mounting hole and screwing the universal screw to the satellite housing inner wall or the satellite mounting frame in advance in a threaded hole. In other embodiments, the mounting box 500 may also be fixed in the corresponding position by fastening, binding, and the like, and the description is not limited in particular.

The mounting box 500 is used for wrapping and protecting the control management module disposed therein, and the shape thereof may be set to be square, spherical, irregular, etc., and the description is not particularly limited. Preferably, for a regular square micro satellite, the mounting box 500 may be configured as a square or rectangular parallelepiped, and the center thereof is a hollow structure so that the control management module can be mounted therein. Also, to facilitate the installation of the control management module, a mounting table 510 (shown in fig. 4) may be provided inside the mounting box 500 in advance to match the bottom profile of the control management module, and the mounting table 510 may be a concave portion that is concave inward according to the bottom profile of the circuit board of the control management module. Meanwhile, corresponding assembly holes are previously provided around the concave portion of the mounting stage 510 in accordance with the fixing position of the control management module, so that an engineer can fix the control management module to the mounting stage 510 using materials such as screws when installing the control management module.

Preferably, at least one flange protruding outward is disposed on the peripheral side of the mounting block 510, and a plurality of positioning holes arranged in a certain arrangement are correspondingly disposed on the peripheral side surface of the mounting box 520 according to the shape of the flange. The mounting table 510 is inserted and fixed between the plurality of peripheral sides of the mounting box 520 through the shape matching of the flange and the positioning hole, and the positioning hole has different positions, so that the advantage that the height of the mounting table 510 in the mounting box 520 can be freely adjusted is realized.

Preferably, for the purpose of connecting the control management module to the solar battery, the storage battery and the electric equipment, a plurality of circuit sockets 530 are respectively formed on the mounting box 500, and due to the above connection requirement, the circuit sockets 530 at least include a solar battery negative socket, a solar battery positive socket, a bus bar positive socket, a storage battery negative socket and an electric equipment negative socket. In the operation of electrifying the control management module, the negative pole and the positive pole of the solar battery pack are respectively and electrically connected to the negative pole socket of the solar battery pack and the positive pole socket of the solar battery pack, the positive pole and the negative pole of the storage battery pack are respectively and electrically connected to the positive pole socket of the bus and the negative pole socket of the storage battery pack, and the positive pole and the negative pole of the electric equipment are respectively and electrically connected to the positive pole socket of the bus and the negative pole socket of the electric equipment. The bus is a bus, so that only one bus socket is arranged, and other sockets can be correspondingly arranged if a multi-bus design is adopted. The other ends of the sockets are electrically connected to corresponding receiving points on the control management module. Preferably, the mounting box 500 may be made of a relatively hard material, such as an aircraft aluminum material, a steel material, or an engineering plastic, and the description is not limited in particular.

Preferably, in order to prevent the control management module in the installation box 500 from being affected by electromagnetic radiation of other high-power and high-current devices on the satellite or cosmic radiation diffused outward by other high-energy satellites in space to cause electromagnetic interference of electronic components in the control management module, a shielding layer 520 capable of wrapping the management module in the module is further arranged inside the installation box 500. The shielding layer 520 covers the control management module, and preferably, the shielding layer 520 may be disposed in a manner of adhering to the inner wall of the mounting box 500, which is equivalent to adding a covering structure on the inner wall of the mounting box 500. Preferably, the shielding layer 520 includes a wave-absorbing material for absorbing electromagnetic waves emitted from the outside to the mounting box 500, so as to prevent the electromagnetic waves from penetrating through the shielding layer 520 and affecting the electronic components of the control management module. The wave-absorbing material can be a wave-absorbing coating formed by a component mixture of carbonyl iron powder, ferrite iron powder and superfine nickel powder, titanium oxide powder and other metal or metal derivative powder through some dispersing aids, the wave-absorbing coating is coated on the surface of the shielding layer 520, the shielding layer 520 is solidified through some processes such as heating and solidification, and a layer structure capable of absorbing electromagnetic waves is finally formed.

It should be noted that the above-mentioned embodiments are exemplary, and that those skilled in the art, having benefit of the present disclosure, may devise various arrangements that are within the scope of the present disclosure and that fall within the scope of the utility model. It should be understood by those skilled in the art that the present specification and figures are illustrative only and are not limiting upon the claims. The scope of the utility model is defined by the claims and their equivalents.

Claims (10)

1. A satellite solar power module comprising:

a solar battery pack (100) electrically connected to the satellite-mounted electric equipment (400) to form a bus for receiving sunlight, performing photoelectric conversion, and supplying electric power to the electric equipment (400),

it is characterized in that the preparation method is characterized in that,

the control management module (200) is electrically connected to the bus in a mode that the control management module collects the output voltage and the output current of the solar battery pack (100) to generate an optimal MPPT control instruction and regulates and controls the output power of the solar battery pack (100) according to the instruction,

the control management module is arranged in the installation box (500), and at least one shielding layer (520) wrapping the control management module (200) and used for shielding external electromagnetic interference is arranged in the installation box (500).

2. The power module as claimed in claim 1, wherein the mounting box (500) is provided with a plurality of circuit sockets (530) according to the connection requirement of the control management module, wherein the circuit sockets (530) at least comprise a solar battery negative socket, a solar battery positive socket, a bus bar positive socket, a storage battery negative socket and a consumer negative socket.

3. The power module as claimed in claim 2, wherein a mounting platform (510) is disposed in the mounting box (500) to match the bottom profile of the control management module, the mounting platform (510) is provided with at least a concave portion that is concave inward according to the bottom profile of the circuit board of the control management module, and the mounting platform (510) is provided with mounting holes for fixing the control management module.

4. A power supply module according to claim 3, wherein a peripheral side of the mounting table (510) is provided with at least one flange protruding outward, a plurality of positioning holes are formed on the peripheral side of the mounting box (500) in a manner matching the shape of the flange, and the mounting table (510) is connected to the mounting box (500) by the flange matching the shape of the positioning holes.

5. The power supply module according to claim 1, wherein the control management module (200) comprises an IC chip (210), wherein the IC chip is electrically connected with the power output of the solar cell set (100).

6. The power module of claim 5, wherein said control management module (200) is composed of at least 2 said IC chips (210), different said IC chips (210) and their associated circuits being independent of each other.

7. The power supply module according to claim 5, wherein the solar cell set (100) is further electrically connectable to a battery pack (300) to form a charging loop when the electrical energy required by the powered device (400) is less than the solar cell set (100), wherein the IC chip (210) is electrically connected to the power input of the battery pack (300).

8. The power supply module according to claim 1, wherein a DC-DC converter is provided between lines electrically connected to the solar cell set (100) by the control management module (200).

9. The power supply module according to claim 7, wherein the IC chip (210) further integrates an SOC detection unit (211), and the SOC detection unit (211) is electrically connected to the battery pack (300).

10. The power module according to claim 8, wherein the control management module further comprises a control loop (220) electrically connected to the IC chip (210), the solar cell set (100), and the battery pack (300), respectively, wherein the DC-DC converter is disposed within the control loop (220).

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