CN116960229A - Preparation method of large-area space full-flexible solar cell array module - Google Patents

Preparation method of large-area space full-flexible solar cell array module Download PDF

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CN116960229A
CN116960229A CN202311157588.7A CN202311157588A CN116960229A CN 116960229 A CN116960229 A CN 116960229A CN 202311157588 A CN202311157588 A CN 202311157588A CN 116960229 A CN116960229 A CN 116960229A
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solar cell
cell array
array module
cerium
glass beads
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吴宜勇
张炜楠
赵会阳
胡克亚
孙承月
赵亮亮
沈文浩
王豪
琚丹丹
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Harbin Institute of Technology
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Harbin Institute of Technology
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    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01L—SEMICONDUCTOR DEVICES NOT COVERED BY CLASS H10
    • H01L31/00—Semiconductor devices sensitive to infrared radiation, light, electromagnetic radiation of shorter wavelength or corpuscular radiation and specially adapted either for the conversion of the energy of such radiation into electrical energy or for the control of electrical energy by such radiation; Processes or apparatus specially adapted for the manufacture or treatment thereof or of parts thereof; Details thereof
    • H01L31/18—Processes or apparatus specially adapted for the manufacture or treatment of these devices or of parts thereof
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01L—SEMICONDUCTOR DEVICES NOT COVERED BY CLASS H10
    • H01L31/00—Semiconductor devices sensitive to infrared radiation, light, electromagnetic radiation of shorter wavelength or corpuscular radiation and specially adapted either for the conversion of the energy of such radiation into electrical energy or for the control of electrical energy by such radiation; Processes or apparatus specially adapted for the manufacture or treatment thereof or of parts thereof; Details thereof
    • H01L31/02—Details
    • H01L31/0236—Special surface textures
    • H01L31/02366—Special surface textures of the substrate or of a layer on the substrate, e.g. textured ITO/glass substrate or superstrate, textured polymer layer on glass substrate
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01L—SEMICONDUCTOR DEVICES NOT COVERED BY CLASS H10
    • H01L31/00—Semiconductor devices sensitive to infrared radiation, light, electromagnetic radiation of shorter wavelength or corpuscular radiation and specially adapted either for the conversion of the energy of such radiation into electrical energy or for the control of electrical energy by such radiation; Processes or apparatus specially adapted for the manufacture or treatment thereof or of parts thereof; Details thereof
    • H01L31/04—Semiconductor devices sensitive to infrared radiation, light, electromagnetic radiation of shorter wavelength or corpuscular radiation and specially adapted either for the conversion of the energy of such radiation into electrical energy or for the control of electrical energy by such radiation; Processes or apparatus specially adapted for the manufacture or treatment thereof or of parts thereof; Details thereof adapted as photovoltaic [PV] conversion devices
    • H01L31/041—Provisions for preventing damage caused by corpuscular radiation, e.g. for space applications
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01L—SEMICONDUCTOR DEVICES NOT COVERED BY CLASS H10
    • H01L31/00—Semiconductor devices sensitive to infrared radiation, light, electromagnetic radiation of shorter wavelength or corpuscular radiation and specially adapted either for the conversion of the energy of such radiation into electrical energy or for the control of electrical energy by such radiation; Processes or apparatus specially adapted for the manufacture or treatment thereof or of parts thereof; Details thereof
    • H01L31/04—Semiconductor devices sensitive to infrared radiation, light, electromagnetic radiation of shorter wavelength or corpuscular radiation and specially adapted either for the conversion of the energy of such radiation into electrical energy or for the control of electrical energy by such radiation; Processes or apparatus specially adapted for the manufacture or treatment thereof or of parts thereof; Details thereof adapted as photovoltaic [PV] conversion devices
    • H01L31/042—PV modules or arrays of single PV cells
    • H01L31/048—Encapsulation of modules

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  • Condensed Matter Physics & Semiconductors (AREA)
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  • Microelectronics & Electronic Packaging (AREA)
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Abstract

The invention discloses a preparation method of a large-area space full-flexible solar cell array module, and belongs to the technical field of space energy systems. The invention aims to solve the problems that the prior flexible solar cell array module has low shielding layer transmittance and output power, can not realize large-area preparation and is easy to debond under actual service conditions. The method comprises the following steps: 1. preparing a flexible polyimide substrate reinforced by pre-buried cables and fiber grids; 2. forming a solar cell array module; 3. coating negative film glue on the flexible polyimide substrate reinforced by the embedded cable and the fiber grid, and placing the solar cell array module on the negative film glue; 4. preparing a mixture of silicone rubber and cerium-containing glass beads; 5. coating a mixture of silicone rubber and cerium-containing glass beads, and laminating for three times; 6. etching or die pressing. The invention is used for preparing the large-area space full-flexible solar cell array module.

Description

Preparation method of large-area space full-flexible solar cell array module
Technical Field
The invention belongs to the technical field of space energy systems.
Background
With the rapid development of the space technology in China, in the fields of manned space, remote sensing detection, space station, deep space exploration and the like, a long-life, high-power and high-reliability space power supply system is one of important challenges facing the space power supply technology in China in the future. The solar cell array is used as a main power supply source of the on-orbit spacecraft, and is one of important components for ensuring the on-orbit power utilization requirement and smooth service of the spacecraft. In recent years, the development of solar cell arrays is mainly implemented in two aspects, on one hand, based on task requirements of space solar power stations, deep space exploration and the like, large-area, light-weight, high-efficiency and high-reliability solar cell arrays need to be developed; on the other hand, the tasks of commercial aerospace, micro-nano satellites, near space aircrafts and the like also provide new challenges for the aspects of light weight, low cost, high integration level and the like of the solar cell array.
The solar cell array is mainly divided into a rigid solar cell array, a semi-rigid solar cell array and a flexible solar cell array. Most on-orbit spacecraft today employ rigid solar cell arrays rather than flexible arrays. The main cause of this phenomenon is: rigid solar cell arrays are highly mature in design from low to medium power range and do not require complex mechanical structures and control mechanisms. However, with the development of long life, high load ratio, high power and lightweight design goals for spacecraft, solar cell arrays are viableThe reliability and power requirements are greatly increased. In this case, there is a limit in design and overall performance of the rigid array due to limitations in the load volume, load weight, launch cost, etc. of the launch vehicle. For example: larger area deployment panels and more complex hinge mechanisms, which further complicate the deployment of rigid arrays in ground assembly and deployment kinematics in a space environment. These limitations make flexible solar arrays more attractive because of its higher volumetric energy density (W/m) than conventional rigid solar arrays 3 ) And specific power (W/kg).
However, the existing prepared flexible solar cell array module has the following defects:
1. the surface shielding material is mainly made of polymer materials (transparent polyimide, polysiloxane film, ETFE film, PTFE film and the like), and the materials are corroded by the radiation of charged particles, atomic oxygen and the like in the space environment, so that the optical performance is easily degraded, and the output power of the solar cell array is reduced;
2. the existing pseudo-type glass cover plate has poorer initial optical performance, the transmittance is only about 85 percent, and the output power of the solar cell array can be greatly lost when the pseudo-type glass cover plate is applied to space.
3. The solar cell array prepared by the lamination process in the prior art is extremely easy to cause debonding phenomenon between cell layers under actual service conditions, thereby causing damage and even failure of cell array components.
Disclosure of Invention
The invention aims to solve the problems that the prior flexible solar cell array module has low shielding layer transmittance and output power, cannot realize large-area preparation and is easy to debond under actual service conditions, and provides a preparation method of a large-area space full-flexible solar cell array module.
The preparation method of the large-area space full-flexible solar cell array module comprises the following steps:
1. slotting the lower surface of the polyimide flexible upper substrate, arranging a cable in the slot, sequentially bonding a fiber grid and the polyimide flexible lower substrate on the lower surface of the polyimide flexible upper substrate, and laminating for one time to obtain a flexible polyimide substrate reinforced by an embedded cable and the fiber grid;
2. the thin film solar cells are connected in series or in parallel by using a resistance welding method to form a solar cell array module;
3. coating negative film glue on the flexible polyimide substrate reinforced by the embedded cable and the fiber grid, and placing the solar cell array module on the negative film glue;
4. mixing silicon rubber with cerium-containing glass beads, then discharging bubbles and standing to obtain a mixture of the silicon rubber and the cerium-containing glass beads;
the particle size of the cerium-containing glass beads is 25.4-78.1 mu m; the mass ratio of the silicon rubber to the cerium-containing glass beads is 1 (0.5-4);
5. coating a mixture of silicon rubber and cerium-containing glass beads, coating the upper surface and the periphery of a solar cell array module to obtain a flexible solar cell array module, and then laminating the flexible solar cell array module for three times by using a laminating machine to obtain a cured flexible solar cell array module;
the three-time lamination is specifically carried out according to the following steps: (1) applying pressure of 30 kPa-200 kPa on the upper side and the lower side of the flexible solar cell array module, and laminating for 10 min-120 min under the conditions that the first lamination temperature is 40-100 ℃ and the pressure on the two sides is 30 kPa-200 kPa;
(2) performing secondary lamination when the temperature is reduced to room temperature, applying pressure of 5kPa to 20kPa on the lower side of the flexible solar cell array module, and laminating for 10min to 120min under the conditions that the room temperature and the lower side pressure are 5kPa to 20 kPa;
(3) applying pressure of 5 kPa-20 kPa on the upper side of the flexible solar cell array module, and laminating for 5-90 min under the conditions of room temperature and 5 kPa-20 kPa on the upper side pressure;
(4) after the pressure of the laminating machine is restored to normal pressure, taking out and curing at room temperature;
6. etching or pressing the cured flexible solar cell array module by a mold to form a surface light trapping structure, thus obtaining a large-area space fully flexible solar cell array module;
the thickness of the embedded cable and the flexible polyimide substrate reinforced by the fiber grid in the large-area space fully flexible solar cell array module is 0.2-0.8 mu m, the thickness of the negative film glue is 50-150 mu m, and the thickness of the mixed layer of the silicon rubber and the cerium-containing glass beads on the upper surface of the solar cell array module is 50-250 mu m.
The beneficial effects of the invention are as follows:
1. according to the invention, the mixture of the silicon rubber and the cerium-containing glass beads is used as the radiation shielding layer, and the mixture filled with the silicon rubber and the cerium-containing glass beads can effectively shield charged particle radiation in a space environment, reduce the electrostatic discharge risk of the solar cell array, improve the discharge threshold value, and improve the anti-radiation performance of the solar cell array and the reliability of the on-orbit service of a spacecraft. The invention modifies the shielding layer on the surface of the solar cell array to form a light trapping structure, and the incident light enters the solar cell to generate a micro-focusing effect, so that the transmittance reaches 93.7% at 560nm of the radiation damage wavelength of the solar cell, the output performance of the solar cell array is further improved, the open-circuit voltage and the short-circuit current of the solar cell array are improved, the short-circuit current of the prepared large-area space fully flexible solar cell array module is 0.46A, the open-circuit voltage is 8.13V, and the maximum power is 3.21W; at an irradiation energy of 1MeV, an irradiation dose rate of 1×10 11 cm- 2 ·s- 1 The irradiation fluence is 1X 10 15 e/cm 2 After electron irradiation under the condition of (1) the short-circuit current is 0.44A, the open-circuit voltage is 7.56V, and the maximum power reaches 2.88W.
2. According to the solar cell array module, the silicon rubber in the shielding layer is used as the bonding layer, so that the problem of stress mismatch of interlayer materials is solved, and the bonding layer is omitted, so that the preparation time and the preparation cost can be greatly shortened.
3. The invention uses a three-time lamination technology, the first lamination is high-temperature and high-pressure lamination, and bubbles among battery array layers are mainly discharged, and the silicone rubber is primarily solidified; after the temperature is restored to the room temperature, the upper layer is fixed by secondary lamination, and the lower layer is pressurized, so that the displacement of the cell array substrate material and the solar cell is avoided; and the lower layer is fixed by three times of lamination, the upper layer is pressurized, the bonding force between the shielding layer and the solar cell is further improved, and the problems of debonding, air bubbles and gassing are avoided. After the three lamination technologies are used, the whole breaking elongation of the solar cell array can reach 124 percent.
4. The invention designs the proper parameters for the specific track: when the service environment is a low-earth orbit, the thicknesses of the embedded cable and the flexible polyimide substrate reinforced by the fiber grid are 0.4-0.8 mu m, the thickness of the mixed layer of the silicon rubber and the cerium-containing glass beads on the upper surface of the solar cell array module is 50-200 mu m, the mass ratio of the silicon rubber to the cerium-containing glass beads is 1 (0.5-4), and the particle size of the cerium-containing glass beads is 21.8-31.8 mu m;
when the service environment is a middle earth orbit, the thicknesses of the embedded cable and the flexible polyimide substrate reinforced by the fiber grid are 0.7-0.8 mu m, the thickness of the mixed layer of the silicon rubber and the cerium-containing glass beads on the upper surface of the solar cell array module is 120-200 mu m, the mass ratio of the silicon rubber to the cerium-containing glass beads is 1 (1-4), and the particle size of the cerium-containing glass beads is 27.4-45.6 mu m;
when the service environment is a geosynchronous orbit, the thicknesses of the embedded cable and the flexible polyimide substrate reinforced by the fiber grid are 0.3-0.8 mu m, the thickness of the mixed layer of the silicon rubber and the cerium-containing glass beads on the upper surface of the solar cell array module is 100-200 mu m, the mass ratio of the silicon rubber to the cerium-containing glass beads is 1 (1-4), and the particle size of the cerium-containing glass beads is 27.4-45.6 mu m;
when the service environment of the large-area space fully-flexible solar cell array module prepared in the step six is a deep space detection track, the thicknesses of the embedded cable and the flexible polyimide substrate reinforced by the fiber grid in the large-area space fully-flexible solar cell array module are 0.5-1.0 mu m, the thickness of the mixed layer of the silicon rubber and the cerium-containing glass beads on the upper surface of the solar cell array module is 180-250 mu m, the mass ratio of the silicon rubber to the cerium-containing glass beads is 1 (1-4), and the particle size of the cerium-containing glass beads is 31.8-55.2 mu m.
5. The invention is thatThe area density of the space flexible solar cell array module using the integrated substrate material and the large-area packaging process is only 660g/m 2 Compared with the traditional rigid solar cell array, the surface density of the solar cell array is reduced by one third, the weight of the solar cell array can be effectively reduced, and the emission cost of a spacecraft is reduced.
In conclusion, the invention effectively reduces the surface density while improving the output power and the elongation at break of the space solar cell array, has radiation shielding performance similar to that of a rigid cover plate, and can effectively improve the service reliability of the spacecraft.
The invention is used for preparing the large-area space full-flexible solar cell array module.
Drawings
Fig. 1 is a side view of an embodiment of a large-area space fully flexible solar cell array module, 1 is a mixed layer of silicone rubber and cerium-containing glass beads, 2 is an electrode, 3 is an anti-reflection coating of the solar cell array module, 4 is the solar cell array module, 5 is an interconnection sheet, 6 is a negative film adhesive, 7 is a polyimide flexible upper substrate, 8 is a cable, and 9 is a polyimide flexible lower substrate containing fiber grids;
fig. 2 is a top view of an embodiment of a large-area space fully flexible solar cell array module, 1 is a mixed layer of silicone rubber and cerium-containing glass beads, 4 is a solar cell array module, 5 is an interconnection sheet, 7 is a polyimide flexible upper substrate, and 10 is a bus cable;
fig. 3 is a comparison of the performance of a solar cell array module (3 cells) encapsulated with a transparent polyimide film before and after irradiation of the solar cell array module (3 cells) of the large-area space fully flexible prepared in example 1, 1 before irradiation of example 1, 2 before irradiation of comparative example 1, 3 after irradiation of example 1, and 4 after irradiation of comparative example 1;
fig. 4 shows the output performance of a large-area space fully flexible solar cell array module (3 cells) with or without a light trapping structure, 1 is a large-area space fully flexible solar cell array module prepared in step six of the embodiment, and 2 is a cured flexible solar cell array module prepared in step five of the embodiment;
FIG. 5 is a graph showing transmittance of a mixed layer of silicone rubber with or without a light trapping structure and cerium-containing glass beads, 1 is a mixed layer of silicone rubber with a light trapping structure and cerium-containing glass beads, and 2 is a mixed layer of silicone rubber without a light trapping structure and cerium-containing glass beads;
fig. 6 is a surface scanning electron microscope of a large-area space fully flexible solar array module (single cell) prepared in example one.
Detailed Description
The technical scheme of the invention is not limited to the specific embodiments listed below, but also includes any combination of the specific embodiments.
The first embodiment is as follows: the preparation method of the large-area space full-flexible solar cell array module is carried out according to the following steps:
1. slotting the lower surface of the polyimide flexible upper substrate, arranging a cable in the slot, sequentially bonding a fiber grid and the polyimide flexible lower substrate on the lower surface of the polyimide flexible upper substrate, and laminating for one time to obtain a flexible polyimide substrate reinforced by an embedded cable and the fiber grid;
2. the thin film solar cells are connected in series or in parallel by using a resistance welding method to form a solar cell array module;
3. coating negative film glue on the flexible polyimide substrate reinforced by the embedded cable and the fiber grid, and placing the solar cell array module on the negative film glue;
4. mixing silicon rubber with cerium-containing glass beads, then discharging bubbles and standing to obtain a mixture of the silicon rubber and the cerium-containing glass beads;
the particle size of the cerium-containing glass beads is 25.4-78.1 mu m; the mass ratio of the silicon rubber to the cerium-containing glass beads is 1 (0.5-4);
5. coating a mixture of silicon rubber and cerium-containing glass beads, coating the upper surface and the periphery of a solar cell array module to obtain a flexible solar cell array module, and then laminating the flexible solar cell array module for three times by using a laminating machine to obtain a cured flexible solar cell array module;
the three-time lamination is specifically carried out according to the following steps: (1) applying pressure of 30 kPa-200 kPa on the upper side and the lower side of the flexible solar cell array module, and laminating for 10 min-120 min under the conditions that the first lamination temperature is 40-100 ℃ and the pressure on the two sides is 30 kPa-200 kPa;
(2) performing secondary lamination when the temperature is reduced to room temperature, applying pressure of 5kPa to 20kPa on the lower side of the flexible solar cell array module, and laminating for 10min to 120min under the conditions that the room temperature and the lower side pressure are 5kPa to 20 kPa;
(3) applying pressure of 5 kPa-20 kPa on the upper side of the flexible solar cell array module, and laminating for 5-90 min under the conditions of room temperature and 5 kPa-20 kPa on the upper side pressure;
(4) after the pressure of the laminating machine is restored to normal pressure, taking out and curing at room temperature;
6. etching or pressing the cured flexible solar cell array module by a mold to form a surface light trapping structure, thus obtaining a large-area space fully flexible solar cell array module;
the thickness of the embedded cable and the flexible polyimide substrate reinforced by the fiber grid in the large-area space fully flexible solar cell array module is 0.2-0.8 mu m, the thickness of the negative film glue is 50-150 mu m, and the thickness of the mixed layer of the silicon rubber and the cerium-containing glass beads on the upper surface of the solar cell array module is 50-250 mu m.
The beneficial effects of this embodiment are:
1. according to the embodiment, the mixture of the silicon rubber and the cerium-containing glass beads is used as the radiation shielding layer, the mixture filled with the silicon rubber and the cerium-containing glass beads can effectively shield charged particle radiation in a space environment, reduce the electrostatic discharge risk of the solar cell array, improve the discharge threshold value, and improve the anti-radiation performance of the solar cell array and the reliability of the on-orbit service of a spacecraft. In addition, the embodiment modifies the shielding layer on the surface of the solar cell array to form a light trapping structure, and the incident light enters the solar cell to generate a micro-focusing effect, so that the transmittance reaches 93.7% at 560nm of the radiation damage wavelength of the solar cell, the output performance of the solar cell array is further improved, and the solar cell array is improved to obtain an open circuitVoltage and short-circuit current, the short-circuit current of the prepared large-area space fully flexible solar cell array module is 0.46A, the open-circuit voltage is 8.13V, and the maximum power is 3.21W; at an irradiation energy of 1MeV, an irradiation dose rate of 1×10 11 cm- 2 ·s- 1 The irradiation fluence is 1X 10 15 e/cm 2 After electron irradiation under the condition of (1) the short-circuit current is 0.44A, the open-circuit voltage is 7.56V, and the maximum power reaches 2.88W.
2. The solar cell array module of the embodiment utilizes the silicon rubber in the shielding layer as the bonding layer, solves the problem of stress mismatch of interlayer materials, and can greatly shorten the preparation time and the preparation cost by omitting the bonding layer.
3. In the embodiment, a three-time lamination technology is used, the first lamination is performed at high temperature and high pressure, bubbles among battery array layers are mainly discharged, and the silicone rubber is subjected to primary solidification; after the temperature is restored to the room temperature, the upper layer is fixed by secondary lamination, and the lower layer is pressurized, so that the displacement of the cell array substrate material and the solar cell is avoided; and the lower layer is fixed by three times of lamination, the upper layer is pressurized, the bonding force between the shielding layer and the solar cell is further improved, and the problems of debonding, air bubbles and gassing are avoided. After the three lamination technologies are used, the whole breaking elongation of the solar cell array can reach 124 percent.
4. The present embodiment designs appropriate parameters for a particular track: when the service environment is a low-earth orbit, the thicknesses of the embedded cable and the flexible polyimide substrate reinforced by the fiber grid are 0.4-0.8 mu m, the thickness of the mixed layer of the silicon rubber and the cerium-containing glass beads on the upper surface of the solar cell array module is 50-200 mu m, the mass ratio of the silicon rubber to the cerium-containing glass beads is 1 (0.5-4), and the particle size of the cerium-containing glass beads is 21.8-31.8 mu m;
when the service environment is a middle earth orbit, the thicknesses of the embedded cable and the flexible polyimide substrate reinforced by the fiber grid are 0.7-0.8 mu m, the thickness of the mixed layer of the silicon rubber and the cerium-containing glass beads on the upper surface of the solar cell array module is 120-200 mu m, the mass ratio of the silicon rubber to the cerium-containing glass beads is 1 (1-4), and the particle size of the cerium-containing glass beads is 27.4-45.6 mu m;
when the service environment is a geosynchronous orbit, the thicknesses of the embedded cable and the flexible polyimide substrate reinforced by the fiber grid are 0.3-0.8 mu m, the thickness of the mixed layer of the silicon rubber and the cerium-containing glass beads on the upper surface of the solar cell array module is 100-200 mu m, the mass ratio of the silicon rubber to the cerium-containing glass beads is 1 (1-4), and the particle size of the cerium-containing glass beads is 27.4-45.6 mu m;
when the service environment of the large-area space fully-flexible solar cell array module prepared in the step six is a deep space detection track, the thicknesses of the embedded cable and the flexible polyimide substrate reinforced by the fiber grid in the large-area space fully-flexible solar cell array module are 0.5-1.0 mu m, the thickness of the mixed layer of the silicon rubber and the cerium-containing glass beads on the upper surface of the solar cell array module is 180-250 mu m, the mass ratio of the silicon rubber to the cerium-containing glass beads is 1 (1-4), and the particle size of the cerium-containing glass beads is 31.8-55.2 mu m.
5. The area density of the space flexible solar cell array module adopting the integrated substrate material and the large-area packaging process in the embodiment is only 660g/m 2 Compared with the traditional rigid solar cell array, the surface density of the solar cell array is reduced by one third, the weight of the solar cell array can be effectively reduced, and the emission cost of a spacecraft is reduced.
In summary, the present embodiment effectively reduces the area density while improving the output power and the elongation at break of the space solar cell array, has radiation shielding performance similar to that of the rigid cover plate, and can effectively improve the service reliability of the spacecraft.
The second embodiment is as follows: the first difference between this embodiment and the specific embodiment is that: the cable in the first step is a copper or gold/silver/nickel alloy cable; the fiber grid in the first step is a glass fiber grid or a carbon fiber grid; sequentially bonding a fiber grid and a polyimide flexible lower substrate by using an adhesive; the primary lamination in the first step is specifically performed according to the following steps: laminating for 20-60 min under the conditions of room temperature and laminating pressure of 20-50 kPa, and finally standing for 24-72 h at room temperature. The other is the same as in the first embodiment.
And a third specific embodiment: this embodiment differs from one or both of the embodiments in that: step two, when the thin film solar cells are connected in series, the inter-series spacing is 1.5 mm-3.5 mm; and in the second step, when the thin film solar cells are connected in parallel, the parallel space is 2 mm-4.5 mm. The other is the same as the first or second embodiment.
The specific embodiment IV is as follows: this embodiment differs from one of the first to third embodiments in that: and in the second step, the thin film solar cell is a copper indium gallium selenium solar cell, a silicon solar cell, a gallium arsenide solar cell or a perovskite solar cell. The other embodiments are the same as those of the first to third embodiments.
Fifth embodiment: this embodiment differs from one to four embodiments in that: and step three, the negative film rubber is silicon rubber. The other embodiments are the same as those of the first to fourth embodiments.
Specific embodiment six: this embodiment differs from one of the first to fifth embodiments in that: in the fourth step, a vacuum chamber or a vacuum deaeration machine is used for foam removal, and standing is carried out for 0.5-3 h; and step four, the doped mass percentage of cerium in the cerium-containing glass beads is 5-25%. The other embodiments are the same as those of the first to fifth embodiments.
Seventh embodiment: this embodiment differs from one of the first to sixth embodiments in that: coating by using a blade coater, a spin coater or a spraying system; and step five (4) curing for 8-60 h at room temperature. The others are the same as in one of the first to sixth embodiments.
Eighth embodiment: this embodiment differs from one of the first to seventh embodiments in that: step six, etching by using ion beam irradiation; and step six, pressing by using a die with a regular triangle surface structure, wherein the height of the regular triangle on the die surface is 0.8-1 μm. The other is the same as in embodiments one to seven.
Detailed description nine: this embodiment differs from one to eight of the embodiments in that: when etching is performed by using ion beam irradiation, the method specifically comprises the following steps:irradiating with argon ion and helium ion plasma source under vacuum degree of 1×10 -4 Pa, 25-55 deg.C, 5-50 keV of irradiation energy and 1X 10 of irradiation dose rate 10 cm -2 ·s -1 ～5×10 12 cm -2 ·s -1 The irradiation fluence is 1 x 10 13 cm -2 ～5×10 15 cm -2 And finally, standing for 8-24 h at room temperature. The others are the same as in embodiments one to eight.
Detailed description ten: this embodiment differs from one of the embodiments one to nine in that: when the service environment of the large-area space fully flexible solar cell array module prepared in the step six is a low earth orbit, the thicknesses of the embedded cable and the flexible polyimide substrate reinforced by the fiber grid in the large-area space fully flexible solar cell array module are 0.4-0.8 mu m, the thickness of the mixed layer of the silicon rubber and the cerium-containing glass beads on the upper surface of the solar cell array module is 50-200 mu m, the mass ratio of the silicon rubber to the cerium-containing glass beads is 1 (0.5-4), and the particle size of the cerium-containing glass beads is 25.4-35.4 mu m;
when the service environment of the large-area space fully flexible solar cell array module prepared in the step six is a middle earth orbit, the thicknesses of the embedded cable and the flexible polyimide substrate reinforced by the fiber grid in the large-area space fully flexible solar cell array module are 0.7-0.8 mu m, the thickness of the mixed layer of the silicon rubber and the cerium-containing glass beads on the upper surface of the solar cell array module is 120-200 mu m, the mass ratio of the silicon rubber to the cerium-containing glass beads is 1 (1-4), and the particle size of the cerium-containing glass beads is 27.4-45.6 mu m;
when the service environment of the large-area space fully flexible solar cell array module prepared in the step six is a geosynchronous orbit, the thicknesses of the embedded cable and the flexible polyimide substrate reinforced by the fiber grid in the large-area space fully flexible solar cell array module are 0.3-0.8 mu m, the thickness of the mixed layer of the silicon rubber and the cerium-containing glass beads on the upper surface of the solar cell array module is 100-200 mu m, the mass ratio of the silicon rubber to the cerium-containing glass beads is 1 (1-4), and the particle size of the cerium-containing glass beads is 27.4-45.6 mu m;
when the service environment of the large-area space fully-flexible solar cell array module prepared in the step six is a deep space detection track, the thicknesses of the embedded cable and the flexible polyimide substrate reinforced by the fiber grid in the large-area space fully-flexible solar cell array module are 0.5-1.0 mu m, the thickness of the mixed layer of the silicon rubber and the cerium-containing glass beads on the upper surface of the solar cell array module is 180-250 mu m, the mass ratio of the silicon rubber to the cerium-containing glass beads is 1 (1-4), and the particle size of the cerium-containing glass beads is 31.8-55.2 mu m. The others are the same as in embodiments one to nine.
The following examples are used to verify the benefits of the present invention:
embodiment one, specifically described with reference to fig. 1 and 2:
the preparation method of the large-area space full-flexible solar cell array module comprises the following steps:
1. slotting the lower surface of the polyimide flexible upper substrate, arranging a cable in the slot, sequentially bonding a fiber grid and the polyimide flexible lower substrate on the lower surface of the polyimide flexible upper substrate, and laminating for one time to obtain a flexible polyimide substrate reinforced by an embedded cable and the fiber grid;
2. the method comprises the steps of connecting electrodes of 60 thin film solar cells and embedded cables through interconnection sheets by using a resistance welding method to form serpentine series connection, and connecting the first thin film solar cell and the second thin film solar cell with bus cables to form a solar cell array module; the inter-string spacing is 2mm;
3. coating negative film glue on the flexible polyimide substrate reinforced by the embedded cable and the fiber grid, and placing the solar cell array module on the negative film glue; the negative film rubber is silicon rubber;
4. mixing silicon rubber with cerium-containing glass beads, then utilizing a vacuum chamber to perform foam removal, and standing for 2 hours to obtain a mixture of the silicon rubber and the cerium-containing glass beads;
5. coating a mixture of silicon rubber and cerium-containing glass beads by using a knife coater, coating the upper surface and the periphery of a solar cell array module to obtain a flexible solar cell array module, and laminating the flexible solar cell array module for three times by using a laminating machine to obtain a cured flexible solar cell array module;
the three-time lamination is specifically carried out according to the following steps: (1) applying pressure of 100kPa on the upper side and the lower side of the flexible solar cell array module, and laminating for 60min under the conditions that the first lamination temperature is 90 ℃ and the pressure on the two sides is 100 kPa;
(2) performing secondary lamination when the temperature is reduced to room temperature, applying pressure of 25kPa on the lower side of the flexible solar cell array module, and laminating for 75 minutes under the conditions that the room temperature and the lower side pressure are 100 kPa;
(3) applying a pressure of-25 kPa on the upper side of the flexible solar cell array module, and laminating for 75 minutes at room temperature under the condition that the upper side pressure is-100 kPa;
(4) after the pressure of the laminating machine is restored to normal pressure, taking out and curing at room temperature for 36 hours;
6. the cured flexible solar cell array module is placed in a vacuum chamber, irradiated by an argon ion source, and the vacuum degree is 1 multiplied by 10 -4 Pa, 25 ℃, irradiation energy of 15keV, and irradiation dose rate of 1×10 11 cm -2 ·s -1 The irradiation fluence is 5 x 10 13 cm -2 And finally standing for 12 hours at room temperature to obtain the large-area space fully flexible solar cell array module;
the thickness of the embedded cable and the flexible polyimide substrate reinforced by the fiber grid in the large-area space fully flexible solar cell array module is 0.8 mu m, the thickness of the negative film glue is 100 mu m, and the thickness of the mixed layer of the silicon rubber and the cerium-containing glass beads on the upper surface of the solar cell array module is 130 mu m.
The fiber grid in the first step is a carbon fiber grid; sequentially bonding a fiber grid and a polyimide flexible lower substrate by using a Nusil-CV1-1142 silicon rubber adhesive; the primary lamination in the first step is specifically performed according to the following steps: laminating for 60min at room temperature under the condition of lamination pressure of 35kPa, and finally standing at room temperature for 48h.
In the second stepThe thin film solar cell is a three-junction thin film gallium arsenide solar cell, the manufacturer is an eighteenth institute of China electronics and technology group, the model is TJ-32, and the electrical performance test method of the solar cell for aerospace is used for measuring the open circuit voltage of the single solar cell to be 2.70V, the short circuit current to be 0.46A, the maximum power point to be 1.07W, the photoelectric conversion efficiency to be 31.76%, the thickness to be 40 μm and the cell area to be 11.75cm 2 。
The negative film rubber in the third step is silicon rubber; the silicone rubber in the third step and the fourth step is DOW 93-500 space-grade silicone rubber.
And step four, the doped mass percentage of cerium in the cerium-containing glass beads is 15%.
When the service environment of the large-area space fully flexible solar cell array module prepared in the step six is a low-earth orbit, the thicknesses of the embedded cable and the flexible polyimide substrate reinforced by the fiber grid in the large-area space fully flexible solar cell array module are 0.4 mu m, the thickness of the mixed layer of the silicon rubber and the cerium-containing glass beads on the upper surface of the solar cell array module is 50 mu m, the mass ratio of the silicon rubber to the cerium-containing glass beads is 1:1, and the particle size of the cerium-containing glass beads is 28.6 mu m; the cable in the first step is a gold/silver/nickel alloy cable;
when the service environment of the large-area space fully flexible solar cell array module prepared in the step six is a middle earth orbit, the thicknesses of the embedded cable and the flexible polyimide substrate reinforced by the fiber grid in the large-area space fully flexible solar cell array module are 0.8 mu m, the thickness of the mixed layer of the silicon rubber and the cerium-containing glass beads on the upper surface of the solar cell array module is 220 mu m, the mass ratio of the silicon rubber to the cerium-containing glass beads is 1:3, and the particle size of the cerium-containing glass beads is 41.8 mu m; the cable in the first step is copper;
when the service environment of the large-area space fully-flexible solar cell array module prepared in the step six is a geosynchronous orbit, the thicknesses of the embedded cable and the flexible polyimide substrate reinforced by the fiber grid in the large-area space fully-flexible solar cell array module are 0.5 mu m, the thickness of the mixed layer of the silicon rubber and the cerium-containing glass beads on the upper surface of the solar cell array module is 150 mu m, the mass ratio of the silicon rubber to the cerium-containing glass beads is 1:2, and the particle size of the cerium-containing glass beads is 38.4 mu m. The cable in the first step is copper;
when the service environment of the large-area space fully-flexible solar cell array module prepared in the step six is a deep space detection track, the thicknesses of the embedded cable and the flexible polyimide substrate reinforced by the fiber grid in the large-area space fully-flexible solar cell array module are 1.0 mu m, the thickness of the mixed layer of the silicon rubber and the cerium-containing glass beads on the upper surface of the solar cell array module is 250 mu m, the mass ratio of the silicon rubber to the cerium-containing glass beads is 1:3, and the particle size of the cerium-containing glass beads is 48.4 mu m; the cable in the first step is a gold/silver/nickel alloy cable.
The large-area space fully flexible solar cell array module prepared by the embodiment uses PET materials for covering protection, and the PET materials are removed before use.
Embodiment two: the first difference between this embodiment and the first embodiment is that: step two, using a resistance welding method, and using interconnection sheets to carry out serpentine series connection on 20 thin film solar cells to form a solar cell array module; spraying a mixture of silicon rubber and cerium-containing glass beads by using vertical spraying equipment under the condition that the spraying air pressure is 1.5kPa, and coating the upper surface and the periphery of the solar cell array module to obtain a flexible solar cell array module; heating the cured flexible solar cell array module at 80 ℃ for 24 hours, pressing the surface of the heated flexible solar cell array module by using a die with a regular triangle surface structure at 80 ℃ for 80 minutes, and finally standing and cooling to obtain the large-area space full-flexible solar cell array module; and the height of the regular triangle of the mold surface was 0.8 μm. The other is the same as in the first embodiment.
Comparative experiment one: the first difference between this comparative experiment and the example is: step five, DOW is utilized93-500 space-level silicone rubber adhesive, transparent polyimide film (++>The model is as follows: cpODA) bonding and coating the upper surface and the periphery of the solar cell array module to obtain a flexible solar cell array module; and then laminating the flexible solar cell array module once by using a laminating machine, and omitting the step five (2) and the step 3 to obtain the cured flexible solar cell array module. The other is the same as in the first embodiment.
Comparison experiment II: the first difference between this comparative experiment and the example is: step five (2) and (3) are omitted. The other is the same as in the first embodiment.
In order to verify the corresponding performance of the large-area space fully flexible solar cell array module, the thin film solar cells in the second step of the adjustment and comparison experiment are single or 3 to form the solar cell array module, and other processes are unchanged;
the electron is irradiated, the irradiation test is carried out according to the GB/T38190-2019 solar cell electron irradiation test method for aerospace, the irradiation energy is 1MeV, and the irradiation dose rate is 1 multiplied by 10 11 cm- 2 ·s- 1 The irradiation fluence is 1X 10 15 e/cm 2 The irradiation parameter can be equivalent to the radiation dose of the solar cell array in 15 years of service in the geosynchronous orbit; fig. 3 is a comparison of the performance of a solar cell array module (3 cells) encapsulated with a transparent polyimide film before and after irradiation of the solar cell array module (3 cells) of the large-area space fully flexible prepared in example 1, 1 before irradiation of example 1, 2 before irradiation of comparative example 1, 3 after irradiation of example 1, and 4 after irradiation of comparative example 1; as can be seen from the graph, the open circuit voltage of the large-area space fully flexible solar cell array module prepared in the first embodiment is 8.13V, the short circuit current is 0.46A, the maximum power is 3.21W, and the comparison experiment shows that the large-area space fully flexible solar cell array module is packaged by using the polyimide filmThe open circuit voltage of the positive cell array module is 8.07V, the short circuit current is 0.42A, and the maximum power is 3.07W; after electron irradiation, the open circuit voltage of the large-area space fully flexible solar cell array module prepared in the embodiment is 7.56V, the short circuit current is 0.44A, the maximum power is 2.88W, and the open circuit voltage of the solar cell array module packaged by the polyimide film is 7.48V, the short circuit current is 0.39A, and the maximum power is 2.69W.
Fig. 4 shows the output performance of a large-area space fully flexible solar cell array module (3 cells) with or without a light trapping structure, 1 is the large-area space fully flexible solar cell array module prepared in step six of the embodiment, and 2 is the cured flexible solar cell array module prepared in step five of the embodiment. As can be seen, the short-circuit current of the solar cell array increases from 0.43A to 0.46A without the light trapping structure due to the light trapping structure.
And (3) curing the mixture of the silicon rubber and the cerium-containing glass beads prepared in the step (IV) of the embodiment for 48 hours at room temperature to obtain a silicon rubber and cerium-containing glass bead mixed layer without a light trapping structure, and then carrying out irradiation modification according to the step (VI) of the embodiment to obtain the silicon rubber and cerium-containing glass bead mixed layer with the light trapping structure. FIG. 5 is a graph showing transmittance of a mixed layer of silicone rubber with or without a light trapping structure and cerium-containing glass beads, 1 is a mixed layer of silicone rubber with a light trapping structure and cerium-containing glass beads, and 2 is a mixed layer of silicone rubber without a light trapping structure and cerium-containing glass beads; the transmittance of the surface structure in the light absorption region of the solar cell was compared with that of the light absorption region of the solar cell, the transmittance of the light trapping structure was 91.2% and the transmittance of the light trapping structure was 93.7% at 560nm of the radiation damage wavelength of the solar cell.
According to GB/T6344-2008 standard, the large-area space full-flexible solar cell array module (single cell) prepared in the first embodiment and the second comparative experiment is subjected to elongation at break test, and after the third lamination technology is used in the first embodiment, the elongation at break of the whole solar cell array is improved from 115% to 124% in the second comparative experiment by the first lamination technology.
The large-area space fully flexible solar cell array module (3 cells) prepared in the first embodiment is measured to obtain a large areaThe area of the integrated space full-flexible solar cell array module is 52.5cm 2 The mass was 3.465g, and thus the areal density was calculated to be 660g/m 2 。
FIG. 6 is a surface scanning electron microscope of a large area space fully flexible solar array module (single cell) prepared in accordance with example one; from the figure, the light trapping structure can be prepared by using the ion beam irradiation method, and the light trapping structure accords with the design requirement.
I-V performance tests are carried out on the large-area space fully flexible solar cell array module prepared in the second embodiment, and the results show that the open circuit voltage of the large-area space fully flexible solar cell array module (3 cells) prepared in the second embodiment is 8.11V, the short circuit current is 0.45A, the maximum power is 3.17W, and the results are similar to those obtained in the first embodiment.

Claims (10)

1. The preparation method of the large-area space full-flexible solar cell array module is characterized by comprising the following steps of:
1. slotting the lower surface of the polyimide flexible upper substrate, arranging a cable in the slot, sequentially bonding a fiber grid and the polyimide flexible lower substrate on the lower surface of the polyimide flexible upper substrate, and laminating for one time to obtain a flexible polyimide substrate reinforced by an embedded cable and the fiber grid;
2. the thin film solar cells are connected in series or in parallel by using a resistance welding method to form a solar cell array module;
3. coating negative film glue on the flexible polyimide substrate reinforced by the embedded cable and the fiber grid, and placing the solar cell array module on the negative film glue;
4. mixing silicon rubber with cerium-containing glass beads, then discharging bubbles and standing to obtain a mixture of the silicon rubber and the cerium-containing glass beads;
the particle size of the cerium-containing glass beads is 25.4-78.1 mu m; the mass ratio of the silicon rubber to the cerium-containing glass beads is 1 (0.5-4);
5. coating a mixture of silicon rubber and cerium-containing glass beads, coating the upper surface and the periphery of a solar cell array module to obtain a flexible solar cell array module, and then laminating the flexible solar cell array module for three times by using a laminating machine to obtain a cured flexible solar cell array module;
the three-time lamination is specifically carried out according to the following steps: (1) applying pressure of 30 kPa-200 kPa on the upper side and the lower side of the flexible solar cell array module, and laminating for 10 min-120 min under the conditions that the first lamination temperature is 40-100 ℃ and the pressure on the two sides is 30 kPa-200 kPa;
(2) performing secondary lamination when the temperature is reduced to room temperature, applying pressure of 5kPa to 20kPa on the lower side of the flexible solar cell array module, and laminating for 10min to 120min under the conditions that the room temperature and the lower side pressure are 5kPa to 20 kPa;
(3) applying pressure of 5 kPa-20 kPa on the upper side of the flexible solar cell array module, and laminating for 5-90 min under the conditions of room temperature and 5 kPa-20 kPa on the upper side pressure;
(4) after the pressure of the laminating machine is restored to normal pressure, taking out and curing at room temperature;
6. etching or pressing the cured flexible solar cell array module by a mold to form a surface light trapping structure, thus obtaining a large-area space fully flexible solar cell array module;
the thickness of the embedded cable and the flexible polyimide substrate reinforced by the fiber grid in the large-area space fully flexible solar cell array module is 0.2-0.8 mu m, the thickness of the negative film glue is 50-150 mu m, and the thickness of the mixed layer of the silicon rubber and the cerium-containing glass beads on the upper surface of the solar cell array module is 50-250 mu m.
2. The method for manufacturing a large-area space fully flexible solar cell array module according to claim 1, wherein the cable in the first step is a copper or gold/silver/nickel alloy cable; the fiber grid in the first step is a glass fiber grid or a carbon fiber grid; sequentially bonding a fiber grid and a polyimide flexible lower substrate by using an adhesive; the primary lamination in the first step is specifically performed according to the following steps: laminating for 20-60 min under the conditions of room temperature and laminating pressure of 20-50 kPa, and finally standing for 24-72 h at room temperature.
3. The method for manufacturing a large-area space fully flexible solar cell array module according to claim 1, wherein in the second step, when the thin film solar cells are connected in series, the inter-string distance is 1.5 mm-3.5 mm; and in the second step, when the thin film solar cells are connected in parallel, the parallel space is 2 mm-4.5 mm.
4. The method for manufacturing a large-area space fully flexible solar cell array module according to claim 1, wherein the thin film solar cell in the second step is a copper indium gallium selenium solar cell, a silicon solar cell, a gallium arsenide solar cell or a perovskite solar cell.
5. The method for manufacturing a large-area space fully flexible solar cell array module according to claim 1, wherein the negative film rubber in the third step is silicone rubber.
6. The method for manufacturing the large-area space fully flexible solar cell array module according to claim 1, wherein the fourth step is to use a vacuum chamber or a vacuum deaerator for foam removal and to stand for 0.5-3 hours; and step four, the doped mass percentage of cerium in the cerium-containing glass beads is 5-25%.
7. The method for manufacturing a large-area space fully flexible solar cell array module according to claim 1, wherein in the fifth step, a blade coater, a spin coater or a spray coating system is used for coating; and step five (4) curing for 8-60 h at room temperature.
8. The method for manufacturing a large-area space fully flexible solar cell array module according to claim 1, wherein in the sixth step, etching is performed by using ion beam irradiation; and step six, pressing by using a die with a regular triangle surface structure, wherein the height of the regular triangle on the die surface is 0.8-1 μm.
9. The method for manufacturing the large-area space fully flexible solar cell array module according to claim 8, wherein the etching is performed by using ion beam irradiation, specifically comprising the following steps: irradiating with argon ion and helium ion plasma source under vacuum degree of 1×10 -4 Pa, 25-55 deg.C, 5-50 keV of irradiation energy and 1X 10 of irradiation dose rate 10 cm -2 ·s -1 ～5×10 12 cm -2 ·s -1 The irradiation fluence is 1 x 10 13 cm -2 ～5×10 15 cm -2 And finally, standing for 8-24 h at room temperature.
10. The method for preparing the large-area space fully flexible solar cell array module according to claim 1, wherein when the service environment of the large-area space fully flexible solar cell array module prepared in the step six is a low-earth orbit, the thicknesses of a pre-buried cable and a flexible polyimide substrate reinforced by fiber grids in the large-area space fully flexible solar cell array module are 0.4-0.8 mu m, the thickness of a mixed layer of silicon rubber and cerium-containing glass beads on the upper surface of the solar cell array module is 50-200 mu m, the mass ratio of the silicon rubber to the cerium-containing glass beads is 1 (0.5-4), and the particle size of the cerium-containing glass beads is 25.4-35.4 mu m;
when the service environment of the large-area space fully flexible solar cell array module prepared in the step six is a middle earth orbit, the thicknesses of the embedded cable and the flexible polyimide substrate reinforced by the fiber grid in the large-area space fully flexible solar cell array module are 0.7-0.8 mu m, the thickness of the mixed layer of the silicon rubber and the cerium-containing glass beads on the upper surface of the solar cell array module is 120-200 mu m, the mass ratio of the silicon rubber to the cerium-containing glass beads is 1 (1-4), and the particle size of the cerium-containing glass beads is 27.4-45.6 mu m;
when the service environment of the large-area space fully flexible solar cell array module prepared in the step six is a geosynchronous orbit, the thicknesses of the embedded cable and the flexible polyimide substrate reinforced by the fiber grid in the large-area space fully flexible solar cell array module are 0.3-0.8 mu m, the thickness of the mixed layer of the silicon rubber and the cerium-containing glass beads on the upper surface of the solar cell array module is 100-200 mu m, the mass ratio of the silicon rubber to the cerium-containing glass beads is 1 (1-4), and the particle size of the cerium-containing glass beads is 27.4-45.6 mu m;
when the service environment of the large-area space fully-flexible solar cell array module prepared in the step six is a deep space detection track, the thicknesses of the embedded cable and the flexible polyimide substrate reinforced by the fiber grid in the large-area space fully-flexible solar cell array module are 0.5-1.0 mu m, the thickness of the mixed layer of the silicon rubber and the cerium-containing glass beads on the upper surface of the solar cell array module is 180-250 mu m, the mass ratio of the silicon rubber to the cerium-containing glass beads is 1 (1-4), and the particle size of the cerium-containing glass beads is 31.8-55.2 mu m.
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CN117677259A (en) * 2024-01-31 2024-03-08 上海伏曦炘空科技有限公司 Perovskite solar cell pasting method and system for space spacecraft

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN117677259A (en) * 2024-01-31 2024-03-08 上海伏曦炘空科技有限公司 Perovskite solar cell pasting method and system for space spacecraft

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