CN216056335U

CN216056335U - Satellite solar power supply standard module with strong expansibility

Info

Publication number: CN216056335U
Application number: CN202122007155.6U
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: 2021-08-24
Filing date: 2021-08-24
Publication date: 2022-03-15
Anticipated expiration: 2031-08-24

Abstract

A satellite solar power standard module with strong expansibility comprises: the solar battery pack is electrically connected with electric equipment on the satellite to form a bus and is used for receiving sunlight, carrying out photoelectric conversion and then supplying electric power to the electric equipment; the control management module is electrically connected to the bus in a mode that the control management module collects output voltage and output current of the solar battery pack to generate an optimal MPPT control instruction and regulates and controls output power of the solar battery pack according to the instruction, the solar battery pack is arranged in the installation fixing plate, and the fixing installation plate makes elastic cushioning support on the solar battery pack according to a mode that an elastic layer arranged at the bottom of the solar battery pack in the fixing installation plate generates elastic deformation during vibration.

Description

Satellite solar power supply standard module with strong expansibility

Technical Field

The utility model relates to a power supply module used by a satellite, in particular to a satellite solar power supply standard module with strong expansibility.

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 MPPT algorithm to carry out output optimization to solar cell array, nevertheless its solar cell panel belongs to the energy center of satellite in the space, has comparatively important value, does not propose the shock attenuation technological means to solar cell panel among this prior art, consequently can cause the solar cell group to lead to the unable normal operating of whole satellite because of the vibration inefficacy.

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 satellite solar power standard module with strong expansibility, which comprises: the solar battery pack is electrically connected with electric equipment on the satellite to form a bus and is used for receiving sunlight, carrying out photoelectric conversion and then supplying electric power to the electric equipment; the control management module is electrically connected to the bus in a mode that the control management module collects output voltage and output current of the solar battery pack to generate an optimal MPPT control instruction and regulates and controls output power of the solar battery pack according to the instruction, the solar battery pack is arranged in an installation fixing plate, and the installation fixing plate makes elastic cushioning support on the solar battery pack according to a mode that an elastic layer arranged at the bottom of the solar battery pack in the installation fixing plate generates elastic deformation during vibration.

Preferably, the mounting fixture plate comprises a base layer and a mounting layer, the elastic layer consisting of a number of springs, one end of the springs being connected to the base layer and the other end being connected to the mounting layer, wherein, when the solar cell set is mounted on the mounting layer, the spring-related parameters of the elastic layer are configured such that the solar cell set is parallel to the ground when the base layer is placed on the ground.

Preferably, the one side that the mounting layer contacted the elastic layer inwards offers the spring groove of corresponding spring quantity according to the mode of the circumference size of size and the spring contact position of cooperation each spring for all springs in the elastic layer all can be connected to inside the spring groove one-to-one.

Preferably, a wrapping layer is sleeved on the periphery of the solar battery pack and the mounting layer, the wrapping layer is configured to be a hollow annular structure with a C-shaped opening configuration in cross section, and the longitudinal dimension of the cross section of the wrapping layer is set according to the sum of the thicknesses of the solar battery pack and the mounting layer.

Preferably, a cover body is arranged on the periphery of the combination formed by the installation layer, the solar battery pack and the elastic layer, the cover body is configured to be of an inverted U-shaped cross section, and a through hole is formed in the bottom of the cover body so that the solar battery pack can receive sunlight through the cover body.

Preferably, the control management module includes an IC chip, wherein the IC chip is electrically connected to the power output terminal of the solar cell set in a manner that the IC chip collects the output voltage and the output current and generates the optimal MPPT command according to an MPPT algorithm stored therein, and the control management module regulates and controls the output power of the solar cell set according to the optimal MPPT command.

Preferably, the control management module is composed of at least 2 IC chips, wherein the 2 IC chips and the circuits matched with the IC chips are independently arranged, so that at least 2 complete sets of IC chips are formed in the control management module.

Preferably, the solar cell array is arranged around the satellite surface in such a way that it can expand the light contact area, wherein the solar cell array can consist of at least one of the following materials: triple junction gallium arsenide (GaInP)₂GaAs/Ge) material, copper indium selenide (CuInSe)₂) Material, Copper Indium Gallium Selenide (CIGS) material and TiO₂A nanocrystalline material made of the material.

Preferably, when the electric power 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, wherein the IC chip is electrically connected to the power input end of the storage battery pack.

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

The utility model has the following beneficial technical effects:

by arranging the mounting and fixing plate with the buffering and damping functions on the peripheral side of the solar battery pack, the solar battery pack which is usually arranged in a plate shape can be relieved from strong vibration in the satellite lifting and in-orbit running processes, and the problem that the solar battery pack is vibrated and fails or fails due to vibration and lack of effective manual maintenance in space is effectively prevented.

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 structural view of a cushioning device and a storage battery case according to the present invention;

FIG. 4 is a front view of the mounting plate of the present invention;

FIG. 5 is a top view of the mounting plate of the present invention;

in the figure: 100. a solar cell array; 200. a control management module; 210. an IC chip; 220. a control loop; 300. a battery pack; 400. an electricity-consuming device; 500. a storage battery case; 600. a cushioning device; 610. a cushioning pad; 620. a shock-absorbing lever; 630. a cushioning frame; 700. mounting a fixed plate; 710. A base layer; 720. an elastic layer; 730. mounting a layer; 740. a wrapping layer; 750. a cover body.

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.

Each solar cell has a sheet-like or plate-like structure in which a certain photoelectric conversion is obtainedThe solar cell can be made of various novel composite materials, such as gallium arsenide triple junction (GaInP)₂GaAs/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 in which the satellite moves around the main satellite is referred to as an illumination period, and at this time, the solar cell set 100 may collect sunlight at 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. 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 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 generally needs to be continuously supplied with power to ensure its normal operation, so that the solar cell set 100 and the battery pack 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.

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, 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.

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 solar cell array is a solar cell windsurfing board arranged on the satellite, which may be in an expandable configuration or in a flat non-collapsible configuration. The solar energy collecting device can also be a plurality of solar energy panels covered on the surface of the satellite, and the solar energy panels are arranged to at least meet the condition that at least one sunward surface of the satellite receives sunlight during the illumination period.

Preferably, in order to protect and limit the storage battery pack, a storage battery box 500 (shown in fig. 3) is arranged around the storage battery pack in a wrapping manner, and according to the arrangement framework of the storage battery pack, the storage battery box 500 may be in a shape of a cuboid, a sphere, an ellipsoid and the like, and preferably, in order to reasonably utilize a small amount of space in a satellite and facilitate manufacturing, the storage battery box 500 is in a cuboid configuration. The battery case 500 may be made of aircraft aluminum, steel, flame retardant resin, etc., and the present invention is not particularly limited.

Preferably, in the satellite launching process and under the condition of in-orbit operation, the satellite and all the components inside the satellite can generate large jitter or vibration, and in order to prevent the battery cells of the storage battery pack from being out of work, performance of the storage battery pack is reduced, internal circuits of the storage battery pack are loosened, and the storage battery pack is damaged by collision, a shock absorption device 600 is arranged outside the storage battery box 500. The cushioning device 600 includes at least one cushioning pad 610 that contacts one of the surfaces of the battery case 500. Preferably, to provide support cushioning in all dimensions of battery case 500, cushioning pads 610 are contacted on all sides of battery case 500. The surface of the shock absorbing pad 610 contacting the battery box 500 is made of a soft material, which can be elastically deformed at least within a certain limit to absorb the vibration damage of the battery box 500. Preferably, the material is a fireproof material with certain elasticity, such as fireproof cotton and fireproof rubber, so as to provide a cushioning function for the storage battery box 500 and achieve a certain flame retardant effect, thereby preventing the storage battery pack from being damaged due to the fire caused by faults, especially the fire caused by chemical batteries which do not need oxygen as a combustion improver. Preferably, under the condition that cabin air is arranged inside the satellite to perform auxiliary heat exchange, a plurality of openings with irregular or regular patterns are formed in the shock absorption pad 610 according to a certain distribution mode, so that the functions of further discharging heat generated by the working of the storage battery pack in the storage battery box 500 and assisting in heat dissipation are realized. Or, one side of the shock absorption pad 610 contacting the storage battery pack is covered with one or more heat dissipation fins, and the heat dissipation fins can adopt a metal fin structure, so that the heat generated by the operation of the storage battery pack is led out by utilizing the advantage of larger outward radiation heat dissipation of metal.

Preferably, a shock absorbing rod 620 is connected to the other side of the shock absorbing pad 610 away from the soft layer contacting the battery box 500, and the connection may be a movable connection manner such as a threaded connection, a snap connection, or a fixed connection manner such as welding or integral generation, and the description is not limited in particular. The shock absorbing rod 620 and the shock absorbing pad 610 together constitute the shock absorbing device 600 described above. This bradyseism pole 620 can adopt the form of ordinary spring to cooperate bradyseism pad 610 to form extra elastic deformation, prevents that great vibration from making battery box 500 or its inside storage battery receive the damage. Preferably, to protect the spring and prevent the smaller and longer spring fixing point from being damaged, so that the spring flies out and flies around to hurt other components on the satellite in the space weightless environment, the shock-absorbing rod 620 may be a spring member with an external telescopic rod structure, and the telescopic rod may protect the spring arranged therein and also prevent the spring from accidentally breaking and flying out. The telescopic link can adopt at least two body that cup joint in order to realize flexible function. In other embodiments, the shock absorbing rod 620 may be a hydraulic or pneumatic rod, which utilizes the hydraulic or pneumatic pressure of the closed space to form a certain elastic support. The other end of the shock rod 620 is connected to the satellite's housing, structural frame or a specially configured shock frame 630, depending on the overall structural design of the satellite. Preferably, a buffering frame 630 is further provided, the buffering frame 630 is disposed at the outer circumference of the battery case 500 and fixed to at least one position inside the satellite, and one end of the buffering rod, which is far from the connection to the buffering pad, is connected to the buffering frame 630. Cushioning frame 630 may at least provide mounting sites for the cushioning rods and cushions so that the combination of cushioning rods and cushions may contact multiple different surfaces of the battery case.

In the case where the buffering means 600 is provided around the battery case 500, in the case where the satellite is set in a rocket for ascent or the satellite is in orbit, the face of the battery case 500 in at least one dimension direction is elastically supported by the buffering means 600 to cancel out the component in at least one direction of vibration generated in the above case. Preferably, the cushioning device 600 is simple and flexible and can be mounted on and in contact with the surface of the battery case 500 in all dimensions to provide all-directional cushioning protection.

Preferably, with respect to vibration protection of the solar cell module 100, a mounting fixture plate 700 (shown in fig. 4 and 5) having at least a multi-layer structure, specifically, at least a base layer 710, an elastic layer 720, a mounting layer 730, and a wrapping layer 740 is provided for the solar cell module 100. The base layer 710 may be a plate-like structure, and a groove is disposed in one area of the base layer, wherein the groove is sized to fit the plate of the solar cell array 100. The inside elastic layer 720 that is provided with of recess, elastic layer 720 can set up to the spring that the several was arranged according to certain mode of arranging, and the spring can be through modes fixed mounting such as welding on the recess bottom surface. Preferably, the springs are arranged in a matrix of rows and columns to obtain optimal cushioning support for the solar cell array. The other portion of the resilient layer 720 that is in contact with the base layer 710 is connected to the mounting layer 730, at least one side of the mounting layer 730 is arranged in full contact with the springs on all of the resilient layers 720, and all of the springs are arranged in the same pattern to achieve the same spring height in a naturally extended condition, so that when the base layer 710 is placed on the ground, the mounting layer 730 supported by the resilient layers 720 is still suspended on the resilient layers 720 in a manner parallel to the ground under the influence of gravity and spring force. Preferably, the surface of the mounting layer 720 contacting the elastic layer 720 is provided with spring slots corresponding to the number of springs inwards in a manner of matching the circumferential dimension and the contact position of each spring, and under such a configuration, all the springs in the elastic layer 720 can be connected to the spring slots in a one-to-one correspondence manner, so as to provide an upward supporting elastic force for the mounting layer 730 and also realize a certain bending prevention protection in the circumferential direction under the semi-wrapping effect of the elastic layer 720.

The solar cell set is disposed on the mounting layer 730, and the connection method may be a screw connection, a welding connection, or other connection methods. Preferably, in order to protect the additional edge of the solar cell and enhance the bonding between the solar cell and the mounting layer 730, a wrapping layer 740 is sleeved around the solar cell and the mounting layer 730, the wrapping layer 740 is configured as a hollow ring structure with a cross section having a C-shaped opening configuration, and the longitudinal dimension of the cross section of the wrapping layer 740 is set in a manner matching the sum of the thicknesses of the solar cell and the mounting layer 730, so that the wrapping layer 740 can further limit the bonding between the solar cell and the mounting layer 730 after wrapping the side edges of the solar cell and the mounting layer 730.

Preferably, in order to realize relative positioning of the combination of the mounting layer 730, the solar cell set, and the elastic layer 720 in the circumferential direction, a cover 750 is interposed on the circumferential sides of the three. Specifically, the cover 750 is configured in a configuration in which a through hole is formed at the bottom of the cover 750 having an inverted U-shaped cross section, wherein when the cover 750 is covered on the solar cell set, the bottom of the cover corresponds to a surface of the top of the solar cell set, which receives sunlight, so that the size of the through hole formed at the bottom of the cover 750 is set in a manner that the light receiving area of the solar cell set is increased as much as possible. In addition, since the inverted U-shaped cover 750 needs to be inserted around the elastic layer 720, the mounting layer 730, and the solar cell array, the size of the groove formed in the base layer 710 is set to at least accept the sum of the thickness of the cover 750 and the maximum side length of the solar cell array or the mounting layer 730 covered with the wrapping layer 740.

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 satellite solar power standard module, comprising:

a solar battery pack (100) which is electrically connected to the satellite-mounted power-using device (400) to form a bus, receives sunlight, performs photoelectric conversion, and supplies electric power to the power-using device (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 solar battery pack (100) is arranged in the installation fixing plate (700), and the installation fixing plate (700) elastically and slowly supports the solar battery pack (100) in a mode that an elastic layer (720) arranged at the bottom of the solar battery pack (100) in the installation fixing plate is elastically deformed during vibration.

2. The power supply standard module according to claim 1, wherein the mounting fixture plate (700) comprises a base layer (710) and a mounting layer (730), the resilient layer (720) consisting of a number of springs connected at one end to the base layer (710) and at the other end to the mounting layer (730), wherein when the solar cell set (100) is mounted on the mounting layer (730), the spring related parameters of the resilient layer (720) are configured such that the base layer (710) is parallel to the ground when placed on the ground.

3. The power standard module according to claim 2, wherein the surface of the mounting layer (730) contacting the elastic layer (720) is provided with spring slots corresponding to the number of the springs in a manner of matching the circumferential dimension and the contact position of each spring, so that all the springs in the elastic layer can be connected to the inside of the spring slots in a one-to-one correspondence manner.

4. The power standard module according to claim 3, wherein a wrapping layer (740) is sleeved around the solar cell set and the mounting layer (730), the wrapping layer (740) is configured as a hollow ring structure with a cross section having a C-shaped opening configuration, and the longitudinal dimension of the cross section of the wrapping layer (740) is set in a manner of matching the sum of the thicknesses of the solar cell set (100) and the mounting layer (730).

5. The power standard module according to claim 4, wherein a cover (750) is disposed around a combination of the mounting layer (730), the solar battery pack and the elastic layer (720), the cover (750) is configured in an inverted U-shaped cross section, and a through hole is formed at the bottom of the cover (750) so that the solar battery pack (100) can receive sunlight through the cover (750).

6. The power standard module according to claim 1, wherein the control management module (200) comprises an IC chip (210), wherein the IC chip (210) is electrically connected to the power output of the solar cell set (100) in such a way that it collects the output voltage and the output current and generates an optimal MPPT command according to an MPPT algorithm stored thereon, and the control management module (200) regulates the output power of the solar cell set (100) according to the optimal MPPT command.

7. The power standard module according to claim 6, wherein the control management module (200) is composed of at least 2 IC chips (210), wherein the 2 IC chips (210) and their associated circuits are independent of each other, so that at least 2 complete sets of IC chips (210) are formed in the control management module (200).

8. The power standard module according to claim 1, wherein the solar cell set (100) is arranged circumferentially above the satellite surface in a manner such that it enables an enlarged optical contact area.

9. The power standard module according to claim 6, 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 electrical 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).

10. The power standard 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).