KR102581067B1 - Manufacturing method of Solar Cell Panel for Satellite - Google Patents

Abstract

The present invention relates to a method of manufacturing solar panels for artificial satellites.
A method of manufacturing a solar cell panel for a satellite according to an example of the present invention includes an adhesion step of attaching a protective film to the front surface, which is the light-receiving surface, of a plurality of solar cells for a plurality of satellites; solar cells for a plurality of satellites in the entire front area of a solar cell array substrate; An application step of applying a cell adhesive made of an insulating material to the cell area where the cell is to be placed; A placement step of arranging a plurality of satellite solar cells with protective films attached to the cell area of the entire front area of the solar cell array substrate; An adhesion step of inserting and sealing a solar array substrate on which a plurality of satellite solar cells are arranged into a vacuum packaging bag, and then vacuum compressing the inside of the vacuum packaging bag to adhere the plurality of satellite solar cells to the solar cell array substrate; and a removal step of removing the protective film from the plurality of satellite solar cells and removing the cell adhesive that has flowed onto the entire surface of the plurality of satellite solar cells in the adhesion step.

Description

Manufacturing method of solar cell panel for satellite {Manufacturing method of Solar Cell Panel for Satellite}

The present invention relates to a method of manufacturing solar panels for artificial satellites.

This invention is a research conducted with the support of the National Research Foundation of Korea-Space Core Technology Development Project funded by the government (Ministry of Science and ICT) in 2018 (NRF-2017M1A3A3A03016626).

Recently, as the depletion of existing energy resources such as oil and coal is predicted, interest in alternative energy to replace them is increasing, and solar cells that produce electrical energy from solar energy are receiving attention.

Such solar cells are widely used as devices that supply power to artificial satellites that perform specific missions in extreme environments.

Accordingly, since solar cell modules for satellites using multiple solar cells operate while exposed to extreme environments, the safety and reliability of solar cell modules that can withstand extreme environments are becoming more important than manufacturing costs.

In particular, solar cell modules applied to artificial satellites must withstand the vibrations generated by the launch vehicle when the satellite is mounted on the launch vehicle and escapes the Earth, and after reaching a specific orbit in space, the satellite is placed in space. After exposure, they must withstand extreme temperatures.

In particular, in outer space, when a satellite is exposed to sunlight, the temperature exceeds +100°C due to the radiant heat of the sun, and when it is not exposed to sunlight and is covered by the Earth's shadow, the temperature is -100°C. As a result, the temperature change range in the rainwater space reaches at least 200℃.

In particular, when the artificial satellite is covered by the shadow of the moon or the Earth and the temperature is below freezing, there is no particular problem with the efficiency of the solar cell. However, when the artificial satellite is exposed to sunlight and the temperature exceeds 100℃ due to the radiant heat of the solar light, the solar cell There is a problem that the efficiency may be reduced.

In such extreme environments, once a breakdown occurs, it cannot be repaired, making the reliability of the solar cell module that supplies power to the satellite even more important.

The purpose of the present invention is to provide a method of manufacturing a solar cell panel for a satellite that can effectively remove contamination on the incident surface of the solar cell and minimize damage.

A method of manufacturing a solar cell panel for a satellite according to an example of the present invention includes an adhesion step of attaching a protective film to the front surface, which is the light-receiving surface, of a plurality of solar cells for a plurality of satellites; solar cells for a plurality of satellites in the entire front area of a solar cell array substrate; An application step of applying a cell adhesive made of an insulating material to the cell area where the cell is to be placed; A placement step of arranging a plurality of satellite solar cells with protective films attached to the cell area of the entire front area of the solar cell array substrate; An adhesion step of inserting and sealing a solar array substrate on which a plurality of satellite solar cells are arranged into a vacuum packaging bag, and then vacuum compressing the inside of the vacuum packaging bag to adhere the plurality of satellite solar cells to the solar cell array substrate; and a removal step of removing the protective film from the plurality of satellite solar cells and removing the cell adhesive that has flowed onto the entire surface of the plurality of satellite solar cells in the adhesion step.

Before the adhesion step, the satellite solar cell has an interconnector connected to an electrode having one polarity among electrodes with different polarities provided in a plurality of satellite solar cells, and a cover is placed on the front of each of the plurality of satellite solar cells. Glass may be attached.

Accordingly, the protective film may be adhered onto the cover glass in the adhesion step.

For example, in the adhesion step, the protective film may be adhered to the front surface of each of the plurality of solar cells for satellites, spaced apart from each other.

More specifically, before the adhesion step, a plurality of solar cells for satellites are formed as long strings connected in series in a first direction by an interconnector, and in the adhesion step, the protective film is longly adhered to the front of the string to cover the entire area of the string. It can be.

Here, the protective film is polyethylene terephthalate (PET), polyimide (PI), polyethylene (PE), polypropylene (PP), polyolefine (PO), and polyvinyl chloride ( It may include a base film containing at least one of polyvinyl chloride (PVC) and an adhesive provided on one side of the base film and containing at least one of an acrylic-based, silicone-based, and olefin-based adhesive.

In addition, the adhesive strength of the adhesive may be between 0.2 N/25mm and 1.0 N/25mm.

Additionally, the thickness of the base film may be between 50um and 100um.

In addition, in the adhesion step, air bubbles existing between the cell adhesive and the solar cell or between the cell adhesive and the solar cell array substrate are removed by vacuum compression of the vacuum packaging bag, and a plurality of satellite solar cells are bonded to the solar array substrate. It can be.

In this adhesion step, the cell adhesive may be cured while overflowing onto the protective film attached to the front surface of the plurality of satellite solar cells by vacuum compression of the vacuum packaging bag.

A method of manufacturing a solar cell panel for a satellite according to an example of the present invention involves attaching a solar cell to a solar cell array substrate with a protective film attached to the front of the solar cell for a satellite, and removing the protective film after attaching the solar cell. By doing so, the cell adhesive spreading over the front of the solar cell can be removed more easily and cleanly.

FIG. 1 briefly illustrates an artificial satellite 1 to which a satellite solar cell 200 panel 10 according to an example of the present invention is applied.
FIG. 2 is a perspective view of the satellite solar cell 200 panel 10 provided on the wing portion of the artificial satellite 1 in FIG. 1 .
Figure 3 is an enlarged view of portion K1 in Figure 2.
Figure 4 is a flow chart for explaining a method of manufacturing a solar cell panel for a satellite according to an example of the present invention.
FIGS. 5 and 6 are diagrams for explaining the structure of the solar cell 200 for a satellite applied to the solar cell panel manufacturing method according to FIG. 4.
FIG. 7 is a diagram for explaining the adhesion step (S1) in FIG. 4, and FIG. 8 shows the protective film 300 adhered to the front of the solar cell 200 for a satellite and a cross-section of the protective film 300. It was done.
FIG. 9 is a diagram for explaining the application step (S2) in FIG. 4.
FIG. 10 is a diagram for explaining the arrangement step (S3) in FIG. 4.
Figures 11 and 12 are diagrams for explaining the adhesion step (S4) in Figure 4.
FIGS. 13A and 13B are diagrams for explaining the removal step (S5) in FIG. 4.

Below, with reference to the attached drawings, embodiments of the present invention will be described in detail so that those skilled in the art can easily implement the present invention. However, the present invention may be implemented in many different forms and is not limited to the embodiments described herein. In order to clearly explain the present invention in the drawings, parts that are not related to the description are omitted, and similar parts are given similar reference numerals throughout the specification.

In the drawing, the thickness is enlarged to clearly express various layers and areas. When a part of a layer, membrane, region, plate, etc. is said to be "on" another part, this includes not only being "directly above" the other part, but also parts in between. Conversely, when a part is said to be “right on top” of another part, it means that there is no other part in between. Also, when a part is said to be formed “wholly” on top of another part, it means not only that it is formed on the entire surface (or front) of the other part, but also that some of the edges are not formed.

In addition, hereinafter, the meaning that the thickness, width, or length of a certain component is the same means that the thickness, width, or length of a first component is compared with the thickness, width, or length of a different second component, taking into account errors in the process. This means that there is an error range of 10%.

Next, the present invention will be described with reference to the attached drawings.

FIG. 1 briefly illustrates an artificial satellite 1 to which a solar cell 200 panel 10 for an artificial satellite according to an example of the present invention is applied, and FIG. 2 is provided on the wing portion of the artificial satellite 1 in FIG. 1. It is a perspective view of the solar cell 200 panel 10 for a satellite, and FIG. 3 is an enlarged view of part K1 in FIG. 2.

As shown in FIG. 1, the solar cell 200 panel 10 for an artificial satellite according to an example of the present invention is located on the wing of the artificial satellite 1 to supply usable power to the artificial satellite 1. It can be applied.

To this end, the satellite solar cell 200 panel 10 located on the wing portion of the artificial satellite 1 includes a solar cell array substrate 100 and a plurality of solar cells 200, as shown in FIG. 2. can do.

Here, the plurality of solar cells 200 may be solar cells 200 for artificial satellites applicable to extreme space environments where temperature changes reach at least 200°C due to radiant heat from solar light.

Unlike the general solar cell 200 used in the Earth's atmosphere, the solar cell 200 for a satellite like this uses a metal material with an extremely low coefficient of thermal expansion as the electrode material, interconnector material, and lead wire material of each solar cell 200. It can be.

In addition, in outer space, unlike on Earth, there is no influence from external wind or climate, so there is no need for a transparent glass substrate to cover the entire plurality of solar cells, and even if a transparent glass substrate is located in front of the solar cell, the glass substrate The plurality of solar cells 200 and interconnectors (not shown) may not be commonly covered.

That is, a transparent glass substrate covers each solar cell 200, but the interconnector is not covered by the glass substrate and may be exposed to outer space.

Accordingly, each solar cell 200 is provided with a cover glass (not shown), a front electrode (not shown), a semiconductor layer for photoelectric conversion (not shown), and a back electrode (not shown), and each front electrode has An interconnector (not shown) may be electrically connected.

In addition, each interconnector (not shown) may connect a plurality of solar cells 200 in series in the first horizontal direction (x) or the second horizontal direction (y).

As shown in FIG. 2, a plurality of such solar cells 200 for artificial satellites may be arranged to be spaced apart in the first horizontal direction (x) and the second horizontal direction (y).

As shown in FIGS. 2 and 3 , the solar cell array substrate 100 supports a plurality of solar cells 200 and can emit radiant heat emitted from the sun. The rear surface of the plurality of solar cells 200 may be adhered to the front surface of the solar cell array substrate 100 using a cell adhesive 400.

1 to 3 briefly look at the solar cell panel for a satellite, but in FIG. 4 and below, a method of manufacturing such a solar cell panel for a satellite will be described.

Figure 4 is a flow chart for explaining a method of manufacturing a solar cell panel for a satellite according to an example of the present invention, and Figures 5 and 6 are a solar cell for a satellite (200) applied to the method for manufacturing a solar cell panel according to Figure 4. ) is a diagram for explaining the structure, and FIG. 7 is a diagram for explaining the adhesion step (S1) in FIG. 4, and FIG. 8 shows the protective film 300 adhered to the front of the solar cell 200 for a satellite. It shows a cross-section of the protective film 300, FIG. 9 is a diagram for explaining the application step (S2) in FIG. 4, FIG. 10 is a diagram for explaining the arrangement step (S3) in FIG. 4, and FIG. 11 and 12 are diagrams for explaining the adhesion step (S4) in FIG. 4, and FIGS. 13A and 13B are diagrams for explaining the removal step (S5) in FIG. 4.

As shown in FIG. 4, the method of manufacturing a solar cell panel for a satellite according to an example of the present invention includes an adhesion step (S1), an application step (S2), a placement step (S3), an adhesion step (S4), and a removal step (S5). It can be included.

FIG. 5 is a perspective view for explaining the structure of the solar cell 200 for a satellite applied to the solar cell panel manufacturing method according to FIG. 4, and FIG. 6 is a first direction (x) of the solar cell 200 shown in FIG. 5. ) It shows a cross-sectional view.

As shown in FIGS. 5 and 6, the solar cell 200 for a satellite includes a semiconductor substrate 240, a front electrode 230, a rear electrode 250, a cover glass 210, and an interconnector 260. In one state, it can be used in the solar panel manufacturing process according to the present invention.

Here, the semiconductor substrate 240 can generate electricity from solar light incident from the outside by forming a p-n junction on the inside, and as shown in FIG. 5 on the front side of the semiconductor substrate 240, in the first horizontal direction The front electrode 230 may be formed including a plurality of finger electrodes extending long in the (x) direction and a bus bar electrode connecting the plurality of finger electrodes extending long in the second direction (y).

In addition, a rear electrode 250 may be formed entirely on the rear surface of the semiconductor substrate 240.

The interconnector 260 has one end electrically connected to the bus bar electrode of the front electrode 230, and the other end extends long in the first horizontal direction and is brought out to the outside of the solar cell 200, as shown in FIG. 6. It can be.

The cover glass 210 may be adhered to the front surface of the semiconductor substrate 240 on which the front electrode 230 is formed using a cover glass adhesive 220 such as transparent epoxy.

As shown in FIGS. 5 and 6, the area of the cover glass 210 has the same area and shape as that of the semiconductor substrate 240, and can be formed by adhering to the front of the semiconductor substrate 240 with the cover glass adhesive 220. there is. Alternatively, the difference between the area of the cover glass 210 and the area of the semiconductor substrate 240 may be within 10%.

Therefore, in the method of manufacturing a solar cell panel according to the present invention, the satellite solar cell 200 is formed by an electrode having one polarity among electrodes with different polarities provided in the plurality of satellite solar cells 200 [for example, , front electrode], an interconnector 260 may be provided, and a cover glass 210 may be attached to the front of each of the plurality of satellite solar cells 200.

That is, from the first and second solar cells 200 adjacent to each other in the first and second horizontal directions (x, y), the cover glass 210 attached to the first solar cell 200 and the second solar cell 200 The attached cover glass 210 may be spaced apart from the first and second solar cells 200 .

In addition, as shown in FIG. 5, the solar cell 200 for a satellite applied to the solar cell panel manufacturing method has some solar cells 200 in each solar cell 200 in addition to the above-described interconnector 260 operating normally. When this is not possible, a bypass wiring 270 that forms a current path that bypasses the solar cell 200 may be additionally provided.

In the adhesion step (S1), as shown in (a) of FIG. 7, the protective film 300 may be adhered to the entire light-receiving surface of the plurality of satellite solar cells 200.

For example, in the adhesion step (S1), the protective film 300 may be adhered onto the cover glass 210 shown in FIGS. 5 and 6.

In the method of manufacturing a solar cell panel according to the present invention, before the adhesion step (S1), the plurality of satellite solar cells 200 are formed as strings connected in series in a long manner in the first horizontal direction by the interconnector 260. You can.

However, the plurality of solar cells 200 are not necessarily limited to being formed into a string before the adhesion step (S1), and the adhesion step (S1) is performed on each solar cell 200 before being formed into a string. It is also possible. However, hereinafter, for convenience of explanation, a case in which the adhesion step (S1) is performed after the plurality of solar cells 200 are formed into a string will be described as an example.

Therefore, when the plurality of solar cells 200 are formed into a string before the adhesion step (S1), as shown in (b) of FIG. 7 in the adhesion step (S1), the protective film 300 is used for a plurality of satellites. The solar cells 200 may be attached to the front surface of each solar cell 200 while being spaced apart from each other.

That is, the protective film 300 may be adhered to the front surface of each of the plurality of solar cells 200 formed as strings, and as a result, the protective film 300 adhered to the front surface of each solar cell 200 may be attached to each solar cell 200. The cells 200 may be spaced apart.

However, the protective film 300 is not necessarily adhered to the entire surface of each solar cell 200 as shown in (b) of FIG. 7, and as shown in (c) of FIG. 7, the protective film 300 is protected in the adhesion step (S1). The film 300 can also be attached long in the second direction (y) to the entire surface of the string so as to cover the entire area of the string.

Accordingly, the protective film 300 can be attached to each string so as to cover the entire string at once on the plurality of solar cells 200 formed as strings.

Therefore, due to this, the protective film 300 attached to the front of each solar cell 200 is not spaced between each solar cell 200, but extends long in the second direction (y), and is attached to both ends of each string. The positioned solar cell 200 may be adhered to one protective film 300 .

Compared to the adhesive structure of the protective film 300 shown in (b) of FIG. 7, the adhesive structure of the protective film 300 as shown in (c) of FIG. 7 forms one string with one protective film 300. Since the entire surface of the plurality of solar cells 200 is adhered, the process time of the adhesion step (S1) can be further shortened.

Here, the area of the protective film 300 attached to each solar cell 200 may be larger than the area of the light-receiving surface of each solar cell 200.

For this purpose, as an example, as shown in (a) of FIG. 8, the protective film 300 attached to each solar cell 200 is aligned in the first horizontal direction (x) or the second horizontal direction (y). The length L300 may be greater than the length L200 of the light-receiving surface of each solar cell 200 in the first horizontal direction (x) or the second horizontal direction (y).

Accordingly, when removing the protective film 300 in the removal step (S5), the protective film 300 removal process can be performed more easily.

Such a protective film 300 may include a base film 310 and an adhesive 320, as shown in (b) of FIG. 8 .

The base film 310 is made of polyethylene terephthalate (PET), polyimide (PI), polyethylene (PE), polypropylene (PP), polyolefine (PO), and polyvinyl chloride. (Polyvinyl chloride, PVC).

The adhesive 320 may be provided on one side of the base film 310. The side of the base film 310 provided with the adhesive 320 may be adhered to the glass substrate of the solar cell 200.

Such adhesive 320 may be formed including at least one of acrylic-based, silicone-based, and olefin-based.

The adhesive strength of the adhesive 320 may be between 0.2 N/25mm and 1.0 N/25mm. Accordingly, after the base film 310 is adhered to the glass substrate of the solar cell 200 and the solar cell 200 is adhered to the solar cell array substrate 100, when the protective film 300 is removed, The solar cell 200 can be prevented from being damaged.

In addition, the thickness of the base film 310 may be greater than the thickness of the adhesive 320. For example, the thickness of the base film 310 may be between 50 μm and 100 μm.

In this way, after the protective film 300 is attached to the front of each solar cell 200, the application step (S2) may proceed. However, the application step (S2) is not necessarily limited to being performed after the adhesion step (S1), and it is possible for the adhesion step (S1) and the application step (S2) to be performed simultaneously.

In the application step (S2), as shown in FIG. 9, a cell adhesive 400 made of an insulating material is applied to the cell area where the plurality of satellite solar cells 200 will be placed among the entire front area of the solar cell array substrate 100. It can be applied.

At this time, the cell adhesive 400 is applied in the form of dots to the cell area where the solar cells 200 are to be placed on the front of the solar cell array substrate 100, and between each cell area to which each cell adhesive 400 is applied is may be separated from each other.

Such a cell adhesive 400 may be formed of at least one of an epoxy-based material or a silicon-based material, and may include platinum (Pt) to further improve heat resistance properties in outer space.

At this time, when attaching solar cells to the solar cell array substrate 100, the application rate of the cell adhesive 400 may be 95% or more and less than 100% of the solar cell string.

Thereafter, as shown in FIG. 10, in the arrangement step (S3), a plurality of satellite solar cells 200 to which the protective film 300 is attached are placed on the cell adhesive 400 in the entire front area of the solar cell array substrate 100. ) may be placed spaced apart in the first and second horizontal directions on the applied cell area.

After the arrangement step (S3) is completed, an adhesion step (S4) of adhering the plurality of solar cells 200 to the solar cell array substrate 100 may be performed.

To this end, in the adhesion step (S4), as shown in FIG. 11, the solar cell array substrate 100 on which a plurality of satellite solar cells 200 are arranged is inserted into the vacuum packaging bag 500, and vacuum The packaging bag 500 can be sealed.

Afterwards, the vacuum pump 510 can suck the air inside the vacuum packaging bag 500 and vacuum compress the inside of the vacuum packaging bag 500.

Thereafter, as the cell adhesive 400 hardens, a plurality of satellite solar cells 200 can be adhered to the solar cell array substrate 100.

In this adhesion step (S4), as shown in FIG. 12, the cell adhesive 400 and the solar cell 200 or the cell adhesive 400 and the solar cell are arranged by vacuum compression of the vacuum packaging bag 500. As air bubbles existing between the substrates 100 escape, the cell adhesive 400 may spread, covering the light-receiving surface of each solar cell 200.

Accordingly, as shown in FIG. 12, in the adhesion step (S4), the cell adhesive 400 is attached to the front surface of the plurality of satellite solar cells 200 by vacuum compression of the vacuum packaging bag 500. It can be cured in a state that overflows over the film 300.

Afterwards, as shown in FIG. 13A, a removal step (S5) may be performed.

In the removal step (S5), as shown in FIG. 13, the protective film 300 is removed from the plurality of artificial satellite solar cells 200, and in the adhesion step (S4), as shown in FIG. 13B, the protective film 300 is removed from the plurality of artificial satellite solar cells 200. The cell adhesive 400 flowing out from the front of the satellite solar cell 200 can be removed.

In the present invention, the cell adhesive 400 flowing out from the front of the solar cell 200 can be easily removed through the removal step (S5).

Accordingly, the present invention involves the adhesion step (S1) of adhering the protective film 300 and removing the protective film 300 from the solar cell 200, so that the cell adhesive 400 flows out on the front surface of the solar cell 200. By providing a removal step (S5) for removing, the method of manufacturing a solar cell panel for a satellite can be made easier.

However, as in the present invention, when the adhesion step (S1) for adhering the protective film 300 and the removal step (S5) for removing the protective film 300 are not provided, the solar cell 200 is attached to the solar cell array substrate. After adhering to 100, the front surface of the cover glass 210 provided on each solar cell 200 is cleaned with a separate cleaning towel in order to remove the cell adhesive 400 that flows out on the front surface of each solar cell 200. The cell adhesive 400 must be removed by rubbing. In this case, scratches may occur on the front of the cover glass 210, or the cell adhesive 400 present on the front of the cover glass 210 may not be completely removed. There is a problem.

In addition, there is a problem such as the semiconductor substrate 240 of the solar cell 200 being damaged while removing the cell adhesive 400 by rubbing the front surface of the cover glass 210. However, the manufacturing method according to an example of the present invention has this problem. The same problem can be completely eliminated.

Although the embodiments of the present invention have been described in detail above, the scope of the present invention is not limited thereto, and various modifications and improvements made by those skilled in the art using the basic concept of the present invention defined in the following claims are also possible. It falls within the scope of rights.

Claims (10)

An adhesion step of adhering a protective film to the entire light-receiving surface of a plurality of satellite solar cells;
An application step of applying a cell adhesive made of an insulating material to a cell area where the plurality of solar cells for satellites are to be placed among the entire front area of the solar cell array substrate;
A placement step of arranging the plurality of satellite solar cells to which the protective film is attached in the cell area of the entire front area of the solar cell array substrate;
After inserting and sealing the solar cell array substrate on which the plurality of satellite solar cells are arranged in a vacuum packaging bag, the inside of the vacuum packaging bag is vacuum compressed to adhere the plurality of satellite solar cells to the solar cell array substrate. adhesion step; and
A method of manufacturing a solar cell panel for a satellite comprising a removal step of peeling off the protective film from the plurality of solar cells for a satellite and removing the cell adhesive that flows out onto the front surfaces of the solar cells for a plurality of satellites in the adhesion step. . According to claim 1,
Before the adhesion step
The solar cell for the artificial satellite is
An interconnector is connected to an electrode having any one polarity among electrodes having different polarities provided in the plurality of satellite solar cells, and a cover glass is attached to the front of each of the plurality of satellite solar cells. Method of manufacturing solar panels for satellites. According to clause 2,
A method of manufacturing a solar cell panel for a satellite in which the protective film is adhered onto the cover glass in the adhesion step. According to clause 3,
In the adhesion step, the protective film is adhered to the front surface of each of the plurality of solar cells for a satellite while being spaced apart from each other. According to clause 3,
Before the adhesion step
The plurality of satellite solar cells are formed as long strings connected in series in a first direction by the interconnector,
In the adhesion step, the protective film is long adhered to the entire surface of the string so as to cover the entire area of the string. According to claim 1,
The protective film is
Polyethylene terephthalate (PET), polyimide (PI), polyethylene (PE), polypropylene (PP), polyolefine (PO), polyvinyl chloride (PVC) A base film containing at least one of
A method of manufacturing a solar cell panel for a satellite, which is provided on one side of the base film and includes an adhesive containing at least one of acrylic, silicone, and olefin. According to clause 6,
A method of manufacturing a solar cell panel for a satellite wherein the adhesive strength is between 0.2 N/25mm and 1.0 N/25mm. According to clause 6,
A method of manufacturing a solar cell panel for a satellite wherein the base film has a thickness of between 50um and 100um. According to claim 1,
In the adhesion step, the vacuum packaging bag is vacuum compressed,
Manufacture of a solar cell panel for a satellite in which the plurality of solar cells for a satellite are adhered to the solar cell array substrate while removing air bubbles existing between the cell adhesive and the solar cell or between the cell adhesive and the solar cell array substrate. method. According to clause 9,
In the adhesion step, the vacuum packaging bag is vacuum compressed,
A method of manufacturing a solar cell panel for a satellite wherein the cell adhesive is cured in a state in which the cell adhesive overflows onto the protective film adhered to the front surface of the plurality of solar cells for a satellite.

Images