Solar panel and production method thereof

Abstract

The invention relates to a solar panel, which comprises a first EVA (Ethylene Vinyl Acetate) film, a solar panel body and a second EVA film, and is provided with a first silica gel layer and a second silica gel layer which are formed on the solar panel body in a cold pressing manner, so that the first EVA film and the solar panel body as well as the second EVA film and the solar panel body are bonded. The silica-based glue solution can perfectly fill the gaps among the first EVA film, the solar panel body and the second EVA film, the production quality of the solar panel is ensured, and the silica-based glue solution is easy to cure, and only needs to dry the solar panel at room temperature without heating, so that the thermal damage of a battery can be prevented, the production efficiency of the solar panel is improved, and the production cost is reduced. Meanwhile, heating equipment for heating and curing is not needed, so that the production cost is reduced. The invention further relates to a solar panel production method.

Description

Technical Field

[0001] This application relates to the field of solar panel equipment technology, and in particular to a solar panel and its manufacturing method. Background Technology

[0002] Stratospheric airships, as unique flight platforms, have demonstrated enormous application potential in numerous fields such as communication, meteorological monitoring, and Earth observation. Stratospheric airships typically remain and fly in the stratosphere for extended periods, placing extremely stringent requirements on their energy systems. Solar panels, as a key energy supply device for stratospheric airships, directly affect the stable and efficient operation of the airship.

[0003] Currently, the solar panels used in stratospheric airships are rigid solar panels. The encapsulation process generally involves heat-sealing the solar cells onto the base plate using an EVA film. In the heat-sealing process, the solar cells and the encapsulation material are usually heat-pressed together at a high temperature. This process is not only time-consuming, but also requires high precision in equipment and processes, resulting in high production costs and causing thermal damage to the batteries, which affects production efficiency.

[0004] Therefore, how to prevent thermal damage to batteries and reduce production costs while improving the production efficiency of solar panels is a technical problem that needs to be solved by those skilled in the art. Summary of the Invention

[0005] This application provides a solar panel and a method for manufacturing the same, which prevents thermal damage to the battery and reduces production costs while improving the production efficiency of the solar panel.

[0006] To achieve the above objectives, the present invention provides the following technical solution:

[0007] A solar panel includes a first EVA film, a solar panel body, and a second EVA film, wherein:

[0008] The first EVA film is disposed on the first side of the solar panel body, and a first silicone layer is disposed between the first EVA film and the solar panel body. The first silicone layer is used to bond the first EVA film to the solar panel body.

[0009] The second EVA film is disposed on the second side of the solar panel body, and a second silicone layer is disposed between the second EVA film and the solar panel body. The second silicone layer is used to bond the second EVA film to the solar panel body.

[0010] The first side and the second side are two opposite sides of the solar panel body;

[0011] The first silicone layer and the second silicone layer are cold-pressed onto the solar panel body.

[0012] Optionally, the solar panel further includes a support frame and a connector. The support frame includes a frame and a connecting part. The frame is connected to the edge of the solar panel body to support the solar panel body. The connecting part is connected to the frame and covers a first or second side of the solar panel body. The connector is used to connect the connecting part to the solar panel body.

[0013] Optionally, in the above-mentioned solar panel, the solar panel body includes multiple solar cells, and the solar cells are connected in series. The solar cells are square, and a connection hole is provided between four adjacent solar cells. The connector cooperates with the connection hole.

[0014] Optionally, in the above-mentioned solar panel, the frame is a carbon fiber frame, including a first link, a second link, a third link and a fourth link connected in sequence, and the first link, the second link, the third link and the fourth link are provided with a plurality of mounting holes;

[0015] The connecting part includes a longitudinal tie wire and a transverse tie wire;

[0016] The two ends of the longitudinal pull wire are respectively connected to the mounting holes of the first connecting rod and the third connecting rod;

[0017] The two ends of the horizontal pull wire are respectively connected to the mounting holes of the second connecting rod and the fourth connecting rod;

[0018] The longitudinal and transverse tension wires form a mesh to create multiple squares, the area of ​​which is adapted to the area of ​​the battery cell.

[0019] The position of the intersection point of the longitudinal pull wire and the transverse pull wire corresponds to the position of the connecting hole, and the connector mates with the intersection point.

[0020] Optionally, in the above-mentioned solar panel, the connector includes a metal eyelet and a U-shaped buckle. The metal eyelet includes two oppositely arranged pieces, which are respectively pressed onto the first side and the second side of the solar panel body. The opening of the metal eyelet corresponds to the position of the connecting hole. The two ends of the U-shaped buckle are provided with fins. The two ends of the U-shaped buckle pass through the connecting hole. The fins are snapped onto the edge of the metal eyelet. The junction point is connected to the middle of the U-shaped buckle.

[0021] Optionally, in the above-mentioned solar panel, the longitudinal and transverse pull wires are nylon wires, polyester fiber wires, or gut wires, and the diameter of the longitudinal and transverse pull wires is 1-2 mm, and the grid is a square with a side length of 5-20 cm.

[0022] Optionally, in the above-mentioned solar panel, the thickness of the first EVA film and the second EVA film is 100 to 1000 micrometers.

[0023] The solar panel provided by this invention comprises a first silicone layer and a second silicone layer cold-pressed onto the solar panel body, which bond the first EVA film to the solar panel body and the second EVA film to the solar panel body. Because the silicone-based adhesive has high permeability, it can perfectly fill the gaps between the first EVA film, the solar panel body, and the second EVA film, ensuring the production quality of the solar panel. Furthermore, the silicone-based adhesive is easy to cure, requiring only room temperature drying of the solar panel without heating, thus preventing thermal damage to the battery and improving the production efficiency of the solar panel. At the same time, it eliminates the need for heating equipment for curing, thereby reducing production costs.

[0024] This application also provides a method for producing solar panels, for producing solar panels as described in any of the above claims, comprising:

[0025] Step S1: Uniformly inject silicone-based adhesive between the first EVA film and the solar panel body, and between the second EVA film and the solar panel body, so that the silicone-based adhesive fills the gaps between the first EVA film and the solar panel body, and between the second EVA film and the solar panel body.

[0026] Step S2: Use a pressure device to extrude and encapsulate the first EVA film, the solar panel body, and the second EVA film;

[0027] Step S3: Let the first EVA film, the solar panel body and the second EVA film stand still, and let the silicone-based adhesive cure to form the first silicone layer and the second silicone layer.

[0028] Optionally, in the above solar panel production method, the pressure device includes a first pressure roller and a second pressure roller, wherein the first pressure roller is used to extrude the first EVA film and the second pressure roller is used to extrude the second EVA film;

[0029] Step S2 includes: the first pressure roller and the second pressure roller simultaneously squeeze the first EVA film, the solar panel body and the second EVA film, and the first pressure roller and the second pressure roller repeatedly roll back and forth to fill the gaps between the first EVA film and the solar panel body, and between the second EVA film and the solar panel body.

[0030] Optionally, in the above-described solar panel manufacturing method, the method further includes the following steps before step S1:

[0031] Step S4: Multiple solar cells are wired together, and connection holes are made between four adjacent solar cells;

[0032] The process after step S3 also includes,

[0033] Step S5: Fix the frame of the support bracket to the edge of the solar panel body, and press the metal eyepiece into the connection hole;

[0034] Step S6: Use a connector to pass through the junction of the connecting part of the support frame and the connecting hole to fix the connecting part to the solar panel body.

[0035] The solar panel production method provided by the present invention uses a silicone-based adhesive to fill the gaps between the first EVA film and the solar panel body, and between the second EVA film and the solar panel body. A pressure device extrudes and encapsulates the first EVA film, the solar panel body, and the second EVA film, thereby ensuring the production quality of the solar panel. During the process of the silicone-based adhesive curing to form the first silicone layer and the second silicone layer, no heating equipment is required, thereby reducing the production cost of the solar panel. Attached Figure Description

[0036] The accompanying drawings, incorporated in and forming part of this specification, illustrate embodiments consistent with this application and, together with the description, serve to explain the principles of this application. To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, those skilled in the art can obtain other drawings based on these drawings without creative effort. One or more embodiments are illustrated by way of example through the corresponding images in the accompanying drawings. These exemplary descriptions do not constitute a limitation on the embodiments. Elements with the same reference numerals in the drawings represent similar elements. Unless otherwise stated, the figures in the drawings do not constitute a limitation on scale.

[0037] Figure 1 This is a schematic diagram of the structure of a solar panel provided in an embodiment of this application;

[0038] Figure 2 This is a schematic diagram of the structure of the battery cell provided in the embodiments of this application;

[0039] Figure 3 This is a schematic diagram of the structure of the connection hole provided in an embodiment of this application;

[0040] Figure 4 A perspective view of the solar panel body provided in an embodiment of this application;

[0041] Figure 5 This is a schematic diagram of the support frame provided in an embodiment of this application;

[0042] Figure 6 A perspective view of the support frame provided in the embodiments of this application;

[0043] Figure 7 This is a schematic diagram of the structure of the connector provided in the embodiments of this application;

[0044] Figure 8 A schematic diagram of the cold-press packaging process provided in an embodiment of this application;

[0045] Figure 9 A perspective view of the cold-pressing packaging process provided in an embodiment of this application.

[0046] Explanation of reference numerals in the attached figures:

[0047] 100 solar cells;

[0048] First EVA film 200, second EVA film 201;

[0049] Solar panel body 300, gap 301;

[0050] Frame 400, longitudinal tie wire 401, transverse tie wire 402, junction point 403, mounting hole 404, connecting hole 405, X-shaped structure 406;

[0051] First pressure roller 500, second pressure roller 501;

[0052] Metal eyepiece 600, U-shaped buckle 601. Detailed Implementation

[0053] To make the objectives, technical solutions, and advantages of the embodiments of this application clearer, the technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0054] The following disclosure provides numerous different embodiments or examples for implementing various structures of this application. To simplify the disclosure, specific examples of components and arrangements are described below. These are merely examples and are not intended to limit the scope of this application. Furthermore, reference numerals and / or letters may be repeated in different examples. Such repetition is for simplification and clarity and does not in itself indicate a relationship between the various embodiments and / or arrangements discussed. In addition, various specific examples of processes and materials are provided in this application; however, those skilled in the art will recognize the applicability of other processes and / or the use of other materials.

[0055] For ease of description, spatial relative terms may be used in the text to describe the relative position or movement of one element or feature relative to another element or feature, as shown in the figure. These relative terms include, for example, "inside," "outside," "middle," "outer," "below," "below," "above," "front," "back," etc. Such spatial relative terms are intended to include different orientations of the device in use or operation, other than those depicted in the figure. For example, if the device in the figure undergoes a positional flip, orientation change, or change of motion, these directional indications will change accordingly. For instance, an element described as "below other elements or features" or "below other elements or features" will subsequently be oriented "above other elements or features" or "above other elements or features." Therefore, the example term "below" can include both upper and lower orientations. The device may be otherwise oriented (rotated 90 degrees or in other directions), and the spatial relative descriptors used in the text will be interpreted accordingly.

[0056] See Figures 1-7 This application provides a solar panel, including a first EVA film 200, a solar panel body 300, and a second EVA film 201. The first EVA film 200 is disposed on a first side of the solar panel body 300, and a first silicone layer is disposed between the first EVA film 200 and the solar panel body 300. The first silicone layer is used to bond the first EVA film 200 to the solar panel body 300. The second EVA film 201 is disposed on a second side of the solar panel body 300, and a second silicone layer is disposed between the second EVA film 201 and the solar panel body 300. The second silicone layer is used to bond the second EVA film 201 to the solar panel body 300. The first side and the second side are opposite sides of the solar panel body 300. The first silicone layer and the second silicone layer are cold-pressed onto the solar panel body 300.

[0057] It should be noted that the solar panel of this application is preferably used in stratospheric airships. The solar panel for stratospheric airships has dual requirements for weight and solar energy conversion efficiency. Therefore, the solar panel of this application is a flexible solar panel. The battery cell 100 is preferably a monocrystalline silicon solar cell or a polycrystalline silicon solar cell to ensure high conversion efficiency. According to multiple experiments and data calculations, the conversion efficiency of the solar panel of this application can reach 20-25%. At the same time, the lightweight support frame is adopted to reduce the overall weight. The overall weight is only 1-1.2 kg / m², which improves production efficiency and reduces production costs while ensuring the use requirements of the solar panel for stratospheric airships.

[0058] Specifically, the first silicone layer and the second silicone layer are cured at room temperature with a silicone-based adhesive. The viscosity of the silicone-based adhesive is 1000-5000 mPa·s to ensure adhesion to the first EVA film 200, the solar panel body 300 and the second EVA film 201.

[0059] The solar panel provided by this invention has a first silicone layer and a second silicone layer, which are cold-pressed onto the solar panel body 300. The first EVA film 200 and the solar panel body 300, as well as the second EVA film 201 and the solar panel body 300 are bonded together. Because the silicone adhesive has high permeability, it can perfectly fill the gap 301 between the first EVA film 200, the solar panel body 300 and the second EVA film 201, ensuring the production quality of the solar panel. Moreover, the silicone adhesive is easy to cure, and the solar panel only needs to be dried at room temperature without heating, thereby preventing thermal damage to the battery and improving the production efficiency of the solar panel. At the same time, there is no need to use heating equipment for heating and curing, thereby reducing production costs.

[0060] To optimize the above technical solution, a support frame and a connector are also included. The support frame includes a frame 400 and a connecting part. The frame 400 is connected to the edge of the solar panel body 300 and is used to support the solar panel body 300. The connecting part is connected to the frame 400 and covers the first or second side of the solar panel body 300. The connector is used to connect the connecting part to the solar panel body 300.

[0061] Specifically, the frame 400 is square and snaps onto the edge of the solar panel body 300. The support frame and the solar panel body 300 are detachably connected by connectors. If the solar panel body 300 is damaged, only the cold-sealed solar panel body 300 needs to be replaced, and the support frame can still be used, thereby extending the service life of the support frame and facilitating the maintenance and replacement of the solar panel body 300.

[0062] To optimize the above technical solution, the solar panel body 300 includes multiple solar cells 100, which are connected in series. The solar cells 100 are square, and a connection hole 405 is provided between four adjacent solar cells 100. The connectors are engaged with the connection holes 405.

[0063] Specifically, square solar cells 100 are welded together to form a square array. A connection hole 405 is opened at the center of the intersection of four adjacent solar cells 100, so that the stress points are evenly distributed in the gap blank area of ​​the solar panel body 300, avoiding stress concentration. The diameter of the connection hole 405 is preferably 3mm to meet the fitting requirements of the connector and ensure the stability of the structure.

[0064] To optimize the above technical solution, the frame 400 is a carbon fiber frame 400, including a first link, a second link, a third link, and a fourth link connected in sequence. Multiple mounting holes 404 are provided on the first link, second link, third link, and fourth link. The connecting part includes a longitudinal tension wire 401 and a transverse tension wire 402. The two ends of the longitudinal tension wire 401 are connected to the mounting holes 404 of the first link and the third link, respectively. The two ends of the transverse tension wire 402 are connected to the mounting holes 404 of the second link and the fourth link, respectively. A mesh is formed between the longitudinal tension wire 401 and the transverse tension wire 402 to create multiple squares. The area of ​​each square is adapted to the area of ​​the battery cell 100. The position of the intersection point 403 of the longitudinal tension wire 401 and the transverse tension wire 402 corresponds to the position of the connecting hole 405, and the connector mates with the intersection point 403.

[0065] Specifically, the carbon fiber frame 400 can be processed from L-shaped carbon fiber strips with a side length of 1 to 3 m. The lengths of the first link, second link, third link, and fourth link are preferably 0.5 to 3 m. The operator can open mounting holes 404 with corresponding spacing and size according to the size of the battery cell 100 and the spacing between the battery cells 100. Preferably, the diameter of the mounting hole 404 is 1 to 2 mm. The longitudinal pull wire 401 and the transverse pull wire 402 can pass through and be bound to the mounting hole 404, or they can be installed in the mounting hole 404 through other connection structures. There are no restrictions here.

[0066] Specifically, the area of ​​the grid is adapted to the area of ​​the solar cell 100, and the position of the junction point 403 corresponds to the position of the connection hole 405, so that the connector is located in the installation blank of the solar cell 100 of the solar panel body 300, preventing the connector from interfering with the solar cell 100, thereby ensuring structural stability and ensuring the solar energy conversion efficiency of the solar cell 100.

[0067] Specifically, longitudinal tension wires 401 and transverse tension wires 402 are arranged in a crisscross pattern between the first, second, third, and fourth connecting rods, forming multiple squares. The mesh of longitudinal tension wires 401 and transverse tension wires 402 is directly tensioned and fixed to the frame 400, forming a lightweight load-bearing surface that provides planar tension. Compared to solid panels in existing technologies, this achieves overall weight reduction for the solar panel. This arrangement gives the support frame excellent properties such as high strength, low density, and high modulus, significantly reducing its weight while ensuring sufficient strength and rigidity. The four vertices of the squares are the aforementioned intersection points 403. Connectors connect the mesh and the solar panel body 300 through these intersection points 403, providing better stable support for the overall structure of the solar panel.

[0068] During use, the longitudinal tension wires 401 and transverse tension wires 402 are interwoven to form a square grid. During weaving, care should be taken to maintain uniform tension in the grid, ensuring the side length of each square is approximately 10cm, thus guaranteeing good flatness and stability. After weaving, the grid should be inspected and cleaned to ensure the surface is free of burrs and debris, and that the mounting holes 404 and junction points 403 are secure, ensuring connection stability.

[0069] Furthermore, in order to increase the planar strength and the strength of the carbon fiber frame 400, diagonal ropes can be tensioned diagonally on the carbon fiber frame 400 to form an X-shaped structure 406.

[0070] To optimize the above technical solution, the connector includes a metal eye piece 600 and a U-shaped buckle 601. The metal eye piece 600 includes two oppositely arranged pieces, which are respectively pressed onto the first and second sides of the solar panel body 300. The opening of the metal eye piece 600 corresponds to the position of the connection hole 405. The two ends of the U-shaped buckle 601 are provided with fins. The two ends of the U-shaped buckle 601 pass through the connection hole 405, and the fins are snapped onto the edge of the metal eye piece 600. The junction point 403 is connected to the middle of the U-shaped buckle 601.

[0071] Specifically, the metal eyelet 600 can disperse the stress around the connection hole 405 and prevent the first EVA film 200 or the second EVA film 201 from tearing. The metal eyelet 600 can be made of aluminum, stainless steel or other materials, and the U-shaped buckle 601 can be made of plastic or metal, preferably Teflon, to adapt to the stratospheric application environment.

[0072] Specifically, the metal eye piece 600 is pressed and connected to the solar panel body 300 to ensure good contact and fixation between the metal eye piece 600 and the solar panel body 300. Then, the U-shaped buckle 601 is used to connect the metal eye piece 600 to the junction point 403 of the mesh.

[0073] In use, the two ends of the U-shaped buckle 601 first pass through any two adjacent squares. At this time, the junction point 403 abuts against the middle of the U-shaped buckle 601. Then, the U-shaped buckle 601 moves upward, and the two ends of the U-shaped buckle 601 pass through the connecting hole 405. The fins are snapped and fixed to the edge of the metal eye piece 600. At this time, the junction point 403 is located in the middle of the U-shaped buckle 601 and abuts against the second EVA film 201. The U-shaped buckle 601 connects the mesh and the solar panel body 300.

[0074] The connectors offer advantages such as simple and convenient connection, stable and reliable connection, detachability, and immunity to shrinkage limitations caused by high and low temperatures. The U-shaped clip 601 design simplifies the connection process, enabling a secure connection between the solar panel body 300 and the mesh without the need for complex tools or processes. Furthermore, this connection method provides excellent detachability; when the solar panel body 300 is damaged and needs replacement, simply loosening the clip allows for easy removal of the damaged panel body 300 without replacing the entire solar panel, significantly improving maintainability and cost-effectiveness.

[0075] To optimize the above technical solution, the longitudinal tension thread 401 and the transverse tension thread 402 are made of nylon thread, polyester fiber thread or gut, and the diameter of the longitudinal tension thread 401 and the transverse tension thread 402 is 1 to 2 mm, and the grid is a square with a side length of 5 to 20 cm.

[0076] Specifically, the side length of the square is preferably 10cm to match the size of most of the solar cells 100.

[0077] Specifically, the gut sutures are natural gut sutures.

[0078] Specifically, the tensile strength of the longitudinal tension wire 401 and the transverse tension wire 402 is greater than 100 MPa.

[0079] Specifically, operators can select different materials for the longitudinal tension wire 401 and the transverse tension wire 402 according to their needs (lightweight requirements and rigidity requirements). The longitudinal tension wire 401 and the transverse tension wire 402 can also be made of mixed materials, such as mixed composite wire (nylon + carbon nanotube fiber), to increase tensile strength and reduce wire diameter.

[0080] To optimize the above technical solution, the thickness of the first EVA film 200 and the second EVA film 201 is 100 to 1000 micrometers.

[0081] Specifically, the thickness of the first EVA film 200 and the second EVA film 201 is preferably 300 micrometers to enable the solar panel to have better solar energy conversion efficiency.

[0082] Secondly, see Figure 8 and Figure 9This application also provides a method for producing solar panels, for producing solar panels as described in any of the above claims, comprising:

[0083] Step S1: Silicon-based adhesive is uniformly injected between the first EVA film 200 and the solar panel body 300, and between the second EVA film 201 and the solar panel body 300, so that the silicone-based adhesive fills the gaps 301 between the first EVA film 200 and the solar panel body 300, and between the second EVA film 201 and the solar panel body 300.

[0084] Step S2: Use a pressure device to extrude and encapsulate the first EVA film 200, the solar panel body 300, and the second EVA film 201;

[0085] Step S3: Let the first EVA film 200, the solar panel body 300 and the second EVA film 201 stand still, and let the silicone-based adhesive cure to form the first silicone layer and the second silicone layer.

[0086] Specifically, under normal circumstances, the volume of the silicone adhesive poured in is approximately twice the volume between the first EVA film 200 and the solar panel body 300, and between the second EVA film 201 and the solar panel body 300. During the pouring of the silicone adhesive, it is necessary to maintain its uniformity and fluidity to ensure that the silicone adhesive can fully fill the gap 301 between the EVA film and the battery cell 100. Preferably, the pressure applied by the pressure device to the first EVA film 200, the solar panel body 300, and the second EVA film 201 is 0.1–0.5 MPa, preferably 0.2–0.3 MPa, to ensure sufficient pressure for the silicone adhesive to fully penetrate and bond, while avoiding damage to the battery cell 100. During the extrusion encapsulation, the pressure device (hereinafter referred to as the first pressure roller 500 and the second pressure roller 501) is repeatedly rolled back and forth to saturate the silicone adhesive in the gap 301. If air bubbles appear, silicone adhesive is poured in again, and the excess silicone adhesive is squeezed out by repeated rolling of the pressure device, ensuring uniform adhesive in the gap 301. After extrusion encapsulation, the solar panel is air-dried at room temperature and normal pressure to allow the silicone adhesive to fully cure, completing the cold encapsulation of the solar panel without the need for high-temperature pressure molding as in existing technologies. The cold-encapsulated solar panel not only has excellent photoelectric conversion performance but also a smooth, flat surface, facilitating subsequent installation and connection.

[0087] Specifically, the operator can determine the drying time based on the actual parameters of the first EVA film 200, the second EVA film 201, the solar panel body 300, the first silicone layer, and the second silicone layer. The drying time at room temperature can be 1 to 5 hours.

[0088] The solar panel manufacturing method provided by this invention uses a silicone-based adhesive to fill the gaps 301 between the first EVA film 200 and the solar panel body 300, and between the second EVA film 201 and the solar panel body 300. A pressure device extrudes and encapsulates the first EVA film 200, the solar panel body 300, and the second EVA film 201, thereby ensuring the production quality of the solar panel. During the process of the silicone-based adhesive curing to form the first silicone layer and the second silicone layer, the cold encapsulation process for preparing the solar panel does not require the use of heating equipment, which can better protect the performance of the solar cell 100 and avoid the performance degradation of the solar cell 100 that may be caused by high-temperature treatment, ensuring that the solar panel has a high photoelectric conversion efficiency, while reducing the production cost of the solar panel.

[0089] To optimize the above technical solution, the pressure device includes a first pressure roller 500 and a second pressure roller 501. The first pressure roller 500 is used to extrude the first EVA film 200, and the second pressure roller 501 is used to extrude the second EVA film 201.

[0090] Step S2 includes: the first pressure roller 500 and the second pressure roller 501 simultaneously squeeze the first EVA film 200, the solar panel body 300 and the second EVA film 201, and the first pressure roller 500 and the second pressure roller 501 repeatedly roll back and forth, so that the gaps 301 between the first EVA film 200 and the solar panel body 300 and between the second EVA film 201 and the solar panel body 300 are filled to saturation.

[0091] Specifically, the first pressure roller 500 and the second pressure roller 501 exert opposite forces to simultaneously compress the first EVA film 200 and the second EVA film 201.

[0092] To optimize the above technical solution, the following step is included before step S1:

[0093] Step S4: Multiple solar cells 100 are wired together, and a connection hole 405 is provided between four adjacent solar cells 100.

[0094] The process after step S3 also includes,

[0095] Step S5: Fix the frame 400 of the support bracket to the edge of the solar panel body 300, and press the metal eye piece 600 into the connection hole 405.

[0096] Step S6: Use a connector to pass through the junction point 403 and the connection hole 405 of the support frame's connector to fix the connector to the solar panel body 300.

[0097] The solar panel provided by this invention is designed specifically for stratospheric airships and can adapt to the complex environmental conditions faced by stratospheric airships during high-altitude flight, such as low temperature, low air pressure, and strong ultraviolet radiation. Its lightweight and high-efficiency features can not only be applied to stratospheric airships, but also be extended to other aerospace fields with strict requirements for weight and energy conversion efficiency, and has broad application prospects.

[0098] The specific structure of the solar panel is as described in the above embodiments. Since the solar panel production method adopts all the technical solutions of all the above embodiments, it has at least all the beneficial effects brought by the technical solutions of the above embodiments, which will not be described in detail here.

[0099] It should be noted that the solar panel and its production method provided by this invention can be used in the field of solar panel equipment technology or other fields. Other fields refer to any field other than the field of solar panel equipment technology. The above are merely examples and do not limit the application areas of the solar panel and its production method provided by this invention.

[0100] It should be understood that the terminology used herein is for the purpose of describing particular exemplary embodiments only and is not intended to be limiting. Unless the context clearly indicates otherwise, the singular forms “a,” “an,” and “described” as used herein may also include the plural forms. The terms “comprising,” “including,” “containing,” and “having” are inclusive and therefore indicate the presence of the stated features, steps, operations, elements, and / or components, but do not exclude the presence or addition of one or more other features, steps, operations, elements, components, and / or combinations thereof. The method steps, processes, and operations described herein are not construed as requiring them to be performed in a particular order described or illustrated unless the order of performance is explicitly indicated. It should also be understood that additional or alternative steps may be used.

[0101] Although terms such as first, second, third, etc., may be used in this document to describe multiple elements, components, regions, layers, and / or segments, these elements, components, regions, layers, and / or segments should not be limited by these terms. These terms may be used only to distinguish one element, component, region, layer, or segment from another. Unless the context clearly indicates otherwise, terms such as "first," "second," and other numerical terms used herein do not imply order or sequence. Therefore, the first element, component, region, layer, or segment discussed below may be referred to as the second element, component, region, layer, or segment without departing from the teachings of the exemplary embodiments.

[0102] The above description is merely a specific embodiment of this application, enabling those skilled in the art to understand or implement this application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of this application. Therefore, this application is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features claimed herein.

Claims

1. A solar panel, characterized in that, It includes a first EVA film, a solar panel body, and a second EVA film, wherein: The first EVA film is disposed on the first side of the solar panel body, and a first silicone layer is disposed between the first EVA film and the solar panel body. The first silicone layer is used to bond the first EVA film to the solar panel body. The second EVA film is disposed on the second side of the solar panel body, and a second silicone layer is disposed between the second EVA film and the solar panel body. The second silicone layer is used to bond the second EVA film to the solar panel body. The first side and the second side are two opposite sides of the solar panel body; The first silicone layer and the second silicone layer are cold-pressed onto the solar panel body.

2. The solar panel according to claim 1, characterized in that, It also includes a support frame and a connector. The support frame includes a frame and a connecting part. The frame is connected to the edge of the solar panel body to support the solar panel body. The connecting part is connected to the frame and covers a first or second side of the solar panel body. The connector is used to connect the connecting part to the solar panel body.

3. The solar panel according to claim 2, characterized in that, The solar panel body includes multiple solar cells, which are connected in series. The solar cells are square, and a connection hole is provided between four adjacent solar cells. The connector mates with the connection hole.

4. The solar panel according to claim 3, characterized in that, The frame is a carbon fiber frame, including a first link, a second link, a third link and a fourth link connected in sequence, and multiple mounting holes are provided on the first link, the second link, the third link and the fourth link; The connecting part includes a longitudinal tie wire and a transverse tie wire; The two ends of the longitudinal pull wire are respectively connected to the mounting holes of the first connecting rod and the third connecting rod; The two ends of the horizontal pull wire are respectively connected to the mounting holes of the second connecting rod and the fourth connecting rod; The longitudinal and transverse tension wires form a mesh to create multiple squares, the area of ​​which is adapted to the area of ​​the battery cell. The position of the intersection point of the longitudinal pull wire and the transverse pull wire corresponds to the position of the connecting hole, and the connector mates with the intersection point.

5. The solar panel according to claim 4, characterized in that, The connector includes a metal eyelet and a U-shaped buckle. The metal eyelet includes two oppositely arranged pieces, which are respectively pressed onto the first and second sides of the solar panel body. The opening of the metal eyelet corresponds to the position of the connection hole. The two ends of the U-shaped buckle are provided with fins. The two ends of the U-shaped buckle pass through the connection hole. The fins are snapped onto the edge of the metal eyelet. The junction point is connected to the middle of the U-shaped buckle.

6. The solar panel according to claim 4, characterized in that, The longitudinal and transverse pull lines are made of nylon, polyester fiber, or gut, and the diameter of the longitudinal and transverse pull lines is 1-2 mm. The grid is a square with a side length of 5-20 cm.

7. The solar panel according to claim 1, characterized in that, The thickness of the first EVA film and the second EVA film is 100 to 1000 micrometers.

8. A method for producing solar panels, characterized in that, For producing a solar panel as described in any one of claims 1 to 7, comprising: Step S1: Uniformly inject silicone-based adhesive between the first EVA film and the solar panel body, and between the second EVA film and the solar panel body, so that the silicone-based adhesive fills the gaps between the first EVA film and the solar panel body, and between the second EVA film and the solar panel body. Step S2: Use a pressure device to extrude and encapsulate the first EVA film, the solar panel body, and the second EVA film; Step S3: Let the first EVA film, the solar panel body and the second EVA film stand still, and let the silicone-based adhesive cure to form the first silicone layer and the second silicone layer.

9. The method for producing solar panels according to claim 8, characterized in that, The pressure device includes a first pressure roller and a second pressure roller, wherein the first pressure roller is used to press the first EVA film and the second pressure roller is used to press the second EVA film. Step S2 includes: the first pressure roller and the second pressure roller simultaneously squeeze the first EVA film, the solar panel body and the second EVA film, and the first pressure roller and the second pressure roller repeatedly roll back and forth to fill the gaps between the first EVA film and the solar panel body, and between the second EVA film and the solar panel body.

10. The method for producing solar panels according to claim 8, characterized in that, The steps preceding step S1 also include, Step S4: Multiple solar cells are wired together, and connection holes are made between four adjacent solar cells; The process after step S3 also includes, Step S5: Fix the frame of the support bracket to the edge of the solar panel body, and press the metal eyepiece into the connection hole; Step S6: Use a connector to pass through the junction of the connecting part of the support frame and the connecting hole to fix the connecting part to the solar panel body.

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