CN216489763U

CN216489763U - Novel solar standard module

Info

Publication number: CN216489763U
Application number: CN202122024769.5U
Authority: CN
Inventors: 向晓霞; 杨峰; 任维佳; 杜健
Original assignee: Mianyang Tianyi Space Technology Co ltd
Current assignee: Mianyang Tianyi Space Technology Co ltd
Priority date: 2021-08-25
Filing date: 2021-08-25
Publication date: 2022-05-10
Anticipated expiration: 2031-08-25

Abstract

A novel solar standard module comprising: the solar battery pack is electrically connected with electric equipment on the satellite to form a bus and used for receiving sunlight, carrying out photoelectric conversion and then supplying electric power to the electric equipment, the control management module is electrically connected into the bus, at least one solar battery pack and at least one control management module form a capacity unit, the capacity units can be combined in any number to form a capacity unit group, and the solar battery pack is further provided with wiring devices, wherein the wiring devices are formed by combining the wiring device units, the number of which is equal to that of the capacity units.

Description

Novel solar standard module

Technical Field

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

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 miniature satellite has short design and development period, is convenient for modularization and mass production, and has the advantages that other satellites cannot be widely adopted.

With the development of commercial aerospace, more stringent requirements are put on commercial satellites, and the core appeal of the commercial satellites is 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 MPPT algorithm to carry out output optimization and manage to storage battery charging to the solar array, nevertheless do not do many interpretations to the productivity unit that multiunit solar array and control management module become this prior art of problem that how links to each other with the generating line, especially to the combination form of nimble changeable productivity unit, how utilize the thought design termination aspect of combination, consider the shortcoming among the prior art.

SUMMERY OF THE UTILITY MODEL

In order to solve at least a part of the problems in the prior art, the utility model provides a novel solar standard module, which comprises: the solar battery pack is electrically connected with electric equipment on the satellite to form a bus and used for receiving sunlight, carrying out photoelectric conversion and then supplying electric power to the electric equipment, the control management module is electrically connected into the bus, at least one solar battery pack and at least one control management module form a capacity unit, the capacity units can be combined in any number to form a capacity unit group, and the solar battery pack is further provided with wiring devices, wherein the wiring devices are formed by combining the wiring device units, the number of which is equal to that of the capacity units.

Preferably, the wiring device unit is provided with a data interface group, wherein the data interface group at least comprises a bus interface, a negative interface of the storage battery pack and a negative interface of the electric equipment, the three interfaces are electrically connected to corresponding branch lines of the bus, the negative line of the storage battery pack and the negative line of the electric equipment respectively, and the bus, the negative line of the storage battery pack and the negative line of the electric equipment of each wiring device unit are respectively communicated so that currents flowing from the interface of each wiring device unit to the branch lines can be collected in the three main lines.

Preferably, the bottom of the wiring device unit is provided with connecting blocks, the mapping positions of the connecting blocks arranged on the top surface of the wiring device unit corresponding to the bottom are provided with connecting grooves which are equal in number and matched with the connecting blocks in shape, screw holes for penetrating screws are formed in the connecting blocks, screw channels are correspondingly formed in the connecting grooves corresponding to the positions where the screws penetrate, and two adjacent wiring device units are connected in a fixing reinforcing mode formed by the connecting blocks and the connecting grooves in shape matching and the screws penetrating through the screw holes and entering the screw channels to form wiring requirements at least meeting the two or more capacity units.

Preferably, the control management module includes an IC chip, the IC chip at least includes an MPPT unit, the MPPT unit collects an output voltage and an output current according to the MPPT unit, and is electrically connected to the power output terminal of the solar battery pack in a manner of generating an optimal MPPT instruction according to an MPPT algorithm stored in the MPPT unit, and the control management module regulates and controls the output power of the solar battery pack according to the optimal MPPT instruction.

Preferably, the control management module is composed of a plurality of IC chips which are independent from each other.

Preferably, when the electric energy required by the electric equipment is less 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 IC chip is electrically connected to the power input end of the storage battery pack in a mode of detecting a voltage signal and a current signal of the storage battery pack and generating at least one optimal charging control instruction by combining the voltage signal and the current signal of the storage battery pack according to a charging control strategy program stored on the IC chip.

Preferably, the control management module further comprises a control loop, and the control loop is electrically connected with the solar battery pack, the storage battery pack and the IC chip.

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

Preferably, the IC chip further integrates an SOC detection unit electrically connected to the secondary battery pack in such a manner that it calculates the remaining capacity of the secondary battery pack according to an SOC detection program set thereon.

Preferably, the control circuit is further electrically connected to the electrical equipment, wherein the control circuit is electrically connected to the SOC detection unit in such a manner that the control circuit adaptively adjusts the load intensity of the electrical equipment according to the remaining battery amount detected by the SOC detection unit.

The utility model has the following beneficial technical effects:

through setting up can freely superimposed termination, realized the production capacity unit crowd's that makes up into to the production capacity unit of different quantity wiring demand, greatly promoted the flexibility in the satellite power design process, rationally utilized the installation space in the satellite, adopt modular termination to make the power module after the installation more standardized, clean and tidy, reduce the unnecessary problem of bringing because of numerous and diverse design.

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 the wiring device 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. a wiring device; 510. a wiring device unit; 511. connecting blocks; 512. and connecting the grooves.

Detailed Description

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

Fig. 1 shows a novel solar standard module, which is used for a satellite in space, so that the utility model at least comprises a solar battery pack 100 for acquiring solar energy in space as a main energy source of the satellite. 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, working environment and manufacturing cost of the satellite to which the solar cell set is appliedAnd (4) comprehensively selecting the reference factors such as calculation.

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, the average discharge voltage is about 3.5V, and compared with the average discharge voltage of a nickel-metal hydride storage battery and a nickel-cadmium 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, so that 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.

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 to meet the minimum working requirement of the satellite, and the control circuit 220 is also electrically connected with the power-consuming equipment 400 in this design.

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, for a more highly modular satellite, most of the components are modular. Preferably, a solar electronics module and a control management module electrically connected thereto are provided as a power generation unit, which can be in the form of a separate package to form a separate module assembly. When an engineer assembles the highly modular satellite, one or more capacity units are selected from the stock and assembled to the power bus of the satellite. Since the control management module 200 has high compatibility, it has adjustment to the solar cell sets 100 with different output characteristics so that they can output with maximum power. Therefore, the capacity units can adjust the output voltage to be the uniform bus voltage.

To facilitate the solar cell set 100 and the control management module 200 to form an independent capacity unit which can be stored separately, at least one solar cell set 100 and at least one control management module 200 are packaged together to form a capacity unit which has at least one configuration with a physical housing package. And because the solar cell set needs to be contacted with sunlight, a sailboard or light receiving board mechanism of the solar cell set is arranged on the housing of the energy production unit so that the solar cell set can convert light energy into electric energy. At least one control management module 200 is wrapped inside the housing of the energy production unit, at least one end of the control management module is electrically connected to the positive electrode and the negative electrode of the solar battery pack 100, and the other end of the control management module is used for connecting a bus, the negative electrode of the storage battery pack 300 and the negative electrode of the electric equipment 400, so that at least a bus socket, a negative electrode socket of the storage battery pack and a negative electrode socket of the electric equipment are arranged on the housing of the energy production unit. The three sockets may be formed by different pins of one socket, or may be separately arranged, and this description is not particularly limited. Preferably, the three insertion openings are arranged side by side to obtain high regularity of the cable.

For a satellite that can use a plurality of the capacity units to form a capacity unit group in parallel or in series, a wiring device 500 (shown in fig. 3) that can connect the plurality of capacity units to a bus is provided on the satellite, and the wiring device 500 can be a device having a space volume defined by a box body with a regular configuration, the configuration can be various shapes, and preferably, the wiring device 500 is a device with a rectangular parallelepiped configuration. A plurality of interface groups are arranged on one of the flat surfaces with a large area on the outer surface of the wiring device 500 according to a certain arrangement mode, wherein each interface group corresponds to the function setting of the three sockets, namely, a bus interface, a negative interface of the storage battery pack 300 and a negative interface of the electric equipment 400 are arranged. The three interfaces correspond to the three sockets one by one, and when the sockets are plugged into the interfaces, the electrical connection and the shape matching connection fixation are formed by the matching relationship between the interfaces and the sockets. The function of the electrical connection can be realized by the current conduction of the pins and sockets arranged in the interface and the socket, and the function of the shape-fit connection fixing can be realized by arranging the socket into a cylindrical configuration and arranging the interface into a concave cylindrical groove, and the two functions can be realized in a manner similar to the matching manner of a plurality of socket interfaces such as TYPEC, USB and the like.

Preferably, the sockets and the interfaces can be connected through wires, that is, a wire with one end connected with one socket and the other end connected with one interface is arranged, and the arrangement can enable the wiring device 500 to be flexibly arranged at any position inside the satellite, but at the same time, the problem that the wires are wound and knotted too much or disordered and swing under the condition of zero weight can affect other equipment in the satellite can be caused.

Therefore, preferably, in order to omit the wires so that the three sockets of the capacity unit are directly connected to the three interfaces arranged on the wiring device 500, the arrangement of the sockets of the wiring device 500 is configured according to the installation frame of the capacity unit on the satellite, so that the three sockets on the capacity unit can be exactly butted with the three interfaces of the wiring device 500 in position after the capacity unit is installed into the installation frame preset on the satellite, and the butting can be a plug-in connection. Due to the installation positions of the plurality of capacity units divided by the installation frame preset in the satellite, the interfaces of the wiring device 500 are correspondingly distributed according to the socket positions of the capacity units in the positions, for example, the installation position of the capacity units is limited to a vertical installation mode by the installation frame, and the interfaces of the wiring device 500 are correspondingly distributed according to the vertical installation mode, so that the casing of the wiring device 500 can be set to be a strip shape, the length of one surface of the interface is at least greater than the length of the connection lines of the sockets of all the capacity units, and the strip shape is favorable.

The wiring device 500 at least comprises a bus, a negative electrode line of the storage battery pack and a negative electrode line of the electric equipment, the three lines penetrate through the inside of the wiring device 500, branch lines of the three lines are branched from the line and connected to three interfaces distributed on the wiring device 500, so that current flowing out of each capacity unit can be collected on the bus, or current flowing out of the negative electrode of the storage battery pack and the negative electrode of the electric equipment can be dispersed into each capacity unit through the branch lines of the negative electrode line of the storage battery pack and the negative electrode line of the electric equipment.

Preferably, to flexibly match the final installation form of the capacity units, for example, to cope with the situation that engineers add or subtract a certain number of capacity units to the current capacity unit group to form a new capacity unit group, the wiring device 500 is also correspondingly configured as a flexible stackable wiring device unit 510, as shown in fig. 3. The wiring device unit 510 is configured to be a basic structure that at least meets the docking requirements of a capacity unit, and specifically, includes at least three connectors for connecting with three sockets on the capacity unit. In order to splice the junction device unit 510 with other identical junction device units 510 to form the junction device 500 capable of coping with a plurality of capacity units, the junction device unit 510 is provided at the bottom with connection blocks 511, and the junction device unit 510 is provided at the top face thereof with connection grooves 512 having the same number as the connection blocks 511 and being matched in shape at the mapping positions corresponding to the connection blocks 511 provided at the bottom. A screw hole for passing a screw is opened through the center of the connecting block 511, and correspondingly, a screw channel is opened in the connecting groove 512 corresponding to the position through which the screw passes. The connection groove 512 has a different position according to the position of the connection block 511, and there are many variations in the fixing manner after the connection between them, for example when the connection block 511 is provided at a position near the middle of the terminal unit 510, due to the inconvenience of using a screw fixation with transverse penetration properties, a snap connection may be used, the above-described screw-threaded channel fixing means may be employed when the connection block 511 is provided at the bottom edge of the terminal unit 510, when connection block 511 is positioned at the bottom edge of wiring device unit 510 and is not positioned in a fully welt manner, besides the structure of the screw hole and the screw channel, the connecting groove 512 is provided with an opening at one side close to the top edge of the wiring unit according to the shape of the screw hole, so that the screw can be fixed by the way that the screw hole is penetrated through the opening and then the screw channel is penetrated. The above-described structural arrangement allows an engineer to fix two or more terminal units 510 by stacking them up and down in such a manner that the shape formed between the connection block 511 and the connection groove 512 is fitted to form a preliminary fixation, and then fixing screws to screw channels by passing the screws through screw holes provided in the connection block 511, thereby fixing the two terminal units 510.

For the line arrangement inside the wiring device 500 formed after the wiring device units 510 are spliced, an engineer may choose to thread the wiring device 500 after the splicing of the wiring device units 510 is completed. Preferably, three branch lines respectively and correspondingly connected to the three interfaces are preset in each wiring device unit 510, the three branch lines are respectively communicated with three main line segments, namely, a bus, a negative electrode line of a storage battery pack and a negative electrode line of electric equipment, and electric connection sockets are arranged at the head end and the tail end of each segment, so that when the wiring device units 510 are stacked, the main line segments in the upper and lower wiring device units 510 are ensured to be communicated by corresponding electric connections, wherein the connection mode can adopt a socket mode, and a magnetic suction mode can also be used for auxiliary positioning.

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

1. A novel solar standard 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 into the bus, at least one solar battery pack and at least one control management module form a capacity unit, the capacity units can be combined in any number to form a capacity unit group, a wiring device is further arranged and is formed by combining wiring device units (510) with the same number as the capacity units,

the bottom of the wiring device unit (510) is provided with connecting blocks (511), connecting grooves (512) which are equal in number and matched in shape with the connecting blocks (511) are arranged on the top surface of the wiring device unit (510) corresponding to the mapping positions of the connecting blocks (511) arranged at the bottom, screw holes for passing screws are formed in the connecting blocks (511), screw channels are correspondingly formed in the connecting grooves (512) corresponding to the positions where the screws penetrate, and two adjacent wiring device units (510) are connected in a fixing reinforcing mode formed by the matching of the connecting blocks (511) and the connecting grooves (512) and the fact that the screws penetrate through the screw holes and enter the screw channels to form wiring requirements at least meeting two or more energy production units.

2. The standard module according to claim 1, wherein the junction block unit (510) is provided with a data interface set, wherein the data interface set at least comprises a bus bar interface, a negative electrode interface of the storage battery pack, and a negative electrode interface of the electric device, the three interfaces are electrically connected to corresponding branch lines of the bus bar, the negative electrode line of the storage battery pack, and the negative electrode line of the electric device, respectively, and the bus bar, the negative electrode line of the storage battery pack, and the negative electrode line of the electric device of each junction block unit (510) are respectively communicated so that the current flowing from the interface of each junction block unit (510) to the branch lines can be collected in the corresponding branch lines of the bus bar, the negative electrode line of the storage battery pack, and the negative electrode line of the electric device.

3. The standard module according to claim 2, characterized in that the control management module (200) comprises an IC chip (210), the IC chip (210) comprising at least an MPPT unit thereon.

4. The standard module according to claim 3, wherein the control management module (200) is composed of a plurality of IC chips (210) independently disposed from each other.

5. The standard module of claim 4, wherein the control management module (200) further comprises a control loop (220) electrically connected to the solar cell set (100), the battery pack (300) and the IC chip (210).

6. The standard module according to claim 5, characterized in that a DC-DC converter is arranged between the lines of the control management module (200) electrically connected to the solar cell set (100), wherein the DC-DC converter is arranged in the control loop (220).

7. The standard module according to claim 6, characterized in that the IC chip (210) further integrates an SOC detection unit (211), the SOC detection unit (211) being electrically connected with the battery pack (300).

8. The standard module according to claim 7, wherein the control loop is further electrically connected to the powered device (400), wherein the control loop (220) is electrically connected to the SOC detection unit (211).