CN115832089B - Space flexible solar cell array and packaging method and application thereof - Google Patents
Space flexible solar cell array and packaging method and application thereof Download PDFInfo
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- CN115832089B CN115832089B CN202211725909.4A CN202211725909A CN115832089B CN 115832089 B CN115832089 B CN 115832089B CN 202211725909 A CN202211725909 A CN 202211725909A CN 115832089 B CN115832089 B CN 115832089B
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- 238000004806 packaging method and process Methods 0.000 title claims abstract description 42
- 238000000034 method Methods 0.000 title claims abstract description 27
- 238000009958 sewing Methods 0.000 claims abstract description 70
- 239000000758 substrate Substances 0.000 claims abstract description 37
- 239000010408 film Substances 0.000 claims abstract description 36
- 239000012790 adhesive layer Substances 0.000 claims abstract description 28
- 239000013039 cover film Substances 0.000 claims abstract description 26
- 239000000853 adhesive Substances 0.000 claims abstract description 24
- 230000001070 adhesive effect Effects 0.000 claims abstract description 24
- 239000003365 glass fiber Substances 0.000 claims description 11
- 229920006231 aramid fiber Polymers 0.000 claims description 8
- 239000000463 material Substances 0.000 claims description 7
- 229920000840 ethylene tetrafluoroethylene copolymer Polymers 0.000 claims description 6
- 239000004810 polytetrafluoroethylene Substances 0.000 claims description 6
- 229920001343 polytetrafluoroethylene Polymers 0.000 claims description 6
- JBRZTFJDHDCESZ-UHFFFAOYSA-N AsGa Chemical compound [As]#[Ga] JBRZTFJDHDCESZ-UHFFFAOYSA-N 0.000 claims description 5
- 229910001218 Gallium arsenide Inorganic materials 0.000 claims description 5
- 230000007774 longterm Effects 0.000 claims description 5
- 229920001721 polyimide Polymers 0.000 claims description 5
- 239000011248 coating agent Substances 0.000 claims description 4
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- 229910021419 crystalline silicon Inorganic materials 0.000 claims description 4
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- 229920000647 polyepoxide Polymers 0.000 claims description 2
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- 239000002313 adhesive film Substances 0.000 abstract description 18
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- 239000000741 silica gel Substances 0.000 description 2
- 229910002027 silica gel Inorganic materials 0.000 description 2
- 229910052709 silver Inorganic materials 0.000 description 2
- 239000004332 silver Substances 0.000 description 2
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Classifications
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/50—Photovoltaic [PV] energy
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- Photovoltaic Devices (AREA)
Abstract
The invention provides a space flexible solar cell array and a packaging method and application thereof. The space flexible solar cell array comprises a flexible substrate, an adhesive layer, a solar cell module and a covering film which are sequentially overlapped; the space flexible solar cell array further comprises sewing threads, and the sewing threads are used for fixing the covering film. According to the invention, the cover film is fixed in the space flexible solar cell module through the sewing threads, so that the problems of bubble generation and reliability reduction of the space flexible solar cell module caused by the use of the packaging adhesive film or the adhesive are avoided.
Description
Technical Field
The invention belongs to the technical field of physical power supplies of space power supply systems, and particularly relates to a space flexible solar cell array and a packaging method and application thereof.
Background
The space solar cell array converts solar energy into electric energy by utilizing photoelectric effect, is an energy guarantee for the on-orbit stable operation of the spacecraft, and is used as an outside cabin, and the solar cell array is directly exposed to a severe space environment, so that the requirement on reliability is extremely high.
The traditional solar cell array is of a rigid structure, the substrate, the solar cell and the glass cover plate are all made of rigid materials, and the glass cover plate, the solar cell and the substrate are all glued and fixed by adopting an adhesive. With the development of aerospace technology, light weight, low cost and flexibility become important development directions of space solar cell arrays.
CN106299002a discloses a flexible solar cell module, a preparation method and application thereof. The flexible solar cell module comprises an upper skin, a first packaging adhesive film, a flexible solar cell array, a second packaging adhesive film, a supporting piece, a third packaging adhesive film and a lower skin which are packaged in a hot-pressing mode sequentially from top to bottom, and the supporting piece is a polymethacrylimide foam board. The preparation method comprises the following steps: laminating an upper skin, a first packaging adhesive film, a flexible solar cell array, a second packaging adhesive film, a supporting piece, a third packaging adhesive film and a lower skin in sequence from top to bottom, and then laminating. The flexible solar cell module provided by the technical scheme has the advantages of low surface density, good bending and flexibility, suitability for being attached to an airfoil curved surface, good reliability, no packaging problems such as warping and fragmentation, and the like, and has wide application in space vehicles.
In the flexible solar cell module provided in the prior art, the cover film (also called as an upper skin) and the flexible solar cell array are connected in a bonding or hot-pressing mode usually through an adhesive, but as the substrate, the solar cell and the cover film of the flexible solar cell array are flexible, the solar cell and the substrate are bonded and then are integrally bonded. If the scheme is adopted, the existence of bubbles is difficult to be completely avoided after large-area encapsulation, the bubbles are fatal to space products, and the bubbles can expand under the high vacuum and thermal environment of the earth orbit, so that the flexible laminated structure is layered or the film layer is damaged; secondly, if the product adopting the adhesive or the hot-pressing whole packaging scheme has hidden quality hazards or defects after the manufacture is finished, the product is difficult to carry out local maintenance due to the characteristics of the integral packaging, and the whole board is required to be repaired or scrapped, so that the cost is increased; secondly, the scheme of adopting an adhesive or hot-pressing integral packaging has a potential hidden trouble: there is the interconnection piece between the solar cell, exists the busbar in the subassembly, and these two parts all designs have and subtracts the stress structure, if it is that binder or hot pressing encapsulation of whole can cause to subtract the stress structure to be sealed admittedly, can't exert its effect of reducing stress, very easily takes place fatigue failure, causes the reduction of product reliability.
Meanwhile, in the prior art, a low-viscosity material such as PTFE or ETFE is generally selected as a covering film, and the binding force between the covering film and an adhesive is insufficient, so that the prepared space flexible solar cell array is extremely easy to cause debonding quality problems during ground operation and in-orbit operation.
In summary, how to provide a space flexible solar cell array and a packaging method thereof that can avoid bubble generation, is convenient for local maintenance and has high reliability has become a technical problem to be solved.
Disclosure of Invention
Aiming at the defects of the prior art, the invention aims to provide a space flexible solar cell array and a packaging method and application thereof. According to the invention, through the design of the space flexible solar cell array structure, the cover film is fixed in the space flexible solar cell array through the sewing threads, so that the problems of bubble generation and reliability reduction of the space flexible solar cell assembly caused by the use of the packaging adhesive film are avoided.
To achieve the purpose, the invention adopts the following technical scheme:
in a first aspect, the invention provides a space flexible solar cell array, which comprises a flexible substrate, an adhesive layer, a solar cell module and a covering film which are sequentially overlapped;
the space flexible solar cell array further comprises sewing threads, and the sewing threads are used for fixing the covering film.
According to the invention, through the design of the space flexible solar cell array structure, the cover film is fixed in the space flexible solar cell array through the sewing threads, so that the problems of bubble generation and reliability reduction of the space flexible solar cell array caused by the use of packaging adhesive films or adhesives are avoided.
In the prior art, the cover film is usually fixed on one side of the solar cell array by using an encapsulation adhesive film or an adhesive, or combining a hot pressing method, but the following defects exist in the scheme of preparing the space flexible solar cell module by using the encapsulation adhesive film (or the adhesive) and hot pressing: firstly, in the process of large-area packaging by using packaging adhesive films (or adhesives) or hot pressing, bubbles are inevitably generated, and the bubbles are fatal to space products, so that even tiny bubbles expand under the high vacuum and hot environment of the earth orbit, and the flexible laminated structure is layered or the film layer is damaged; secondly, adopting a packaging adhesive film (or an adhesive) or a product packaged by hot pressing, and after packaging, if a hidden quality trouble or defect is found, the product is difficult to be locally maintained due to the characteristic of integral packaging, and the whole board is required to be repaired or scrapped, so that the cost is increased; thirdly, because the interconnection sheet exists between the solar cell sheets, the bus bar exists in the assembly, and the two parts are designed with the stress reduction structure, if packaging adhesive films (or adhesives) or hot pressing are adopted for packaging, the stress reduction structure is fixedly sealed, the effect of reducing the stress cannot be exerted, fatigue failure is easy to occur, and the reliability of the product is reduced; fourth, in the prior art, PTFE or ETFE or other low-viscosity materials are generally selected as the cover film, and due to the low viscosity of the cover film, the cover film has insufficient bonding force with the packaging adhesive film (or adhesive), so that the prepared space flexible solar cell array is extremely prone to the problem of debonding quality during ground operation and in-orbit operation.
According to the invention, through the use of the sewing threads, the covering film is sewn and fixed in the space flexible solar cell array through the sewing threads, so that the use of an encapsulation adhesive film (or an adhesive) is effectively avoided, and meanwhile, a hot-pressing method is not required to be used, so that the space flexible solar cell array with excellent performance can be prepared, and the problems are effectively solved.
In the present invention, no adhesive layer (e.g., an encapsulating film or an adhesive layer formed of an adhesive) is provided between the solar cell module and the cover film to connect the cover film to one side of the solar cell array.
The following is a preferred technical scheme of the present invention, but not a limitation of the technical scheme provided by the present invention, and the following preferred technical scheme can better achieve and achieve the objects and advantages of the present invention.
In a preferred embodiment of the present invention, the breaking strength of the sewing thread is not less than 2000MPa, for example, 2000MPa, 2100MPa, 2200MPa, 2300MPa, 2400MPa, 2500MPa, 2600MPa, 2700MPa, 2800MPa, 2900MPa, 3000MPa, or the like.
In the invention, the method for testing the breaking strength of the sewing thread can refer to the method for testing the breaking strength in ASTMD 7269.
Preferably, the long-term working temperature of the sewing thread is equal to or higher than 150 ℃, for example, 150 ℃, 155 ℃, 160 ℃, 165 ℃, 170 ℃ and the like.
Preferably, the irradiation resistance of the sewing thread is not less than 100kRad (Si), and for example, 100kRad (Si), 110kRad (Si), 120kRad (Si), 130kRad (Si), 140kRad (Si), 150kRad (Si), 160kRad (Si) or the like can be used.
According to the invention, the irradiation resistance of the sewing thread can be tested by adopting a Co60 gamma radiation source to perform a certain dose irradiation test on the material, and the breaking strength attenuation of the material after the test is not more than 20%.
According to the invention, the prepared space flexible solar cell array can be directly exposed in a severe space environment by selecting the sewing thread with high strength, high temperature resistance and irradiation resistance, and is used in the field of aerospace.
As a preferred embodiment of the present invention, the sewing thread is selected from glass fiber and/or aramid fiber.
Preferably, the diameters of the glass fiber and the aramid fiber are respectively independent and equal to or larger than 25 μm, and can be 25 μm, 27 μm, 30 μm, 33 μm, 35 μm, 38 μm, 40 μm, 42 μm, 46 μm, 50 μm or the like.
Preferably, the sewing thread is of a monofilament structure or a multifilament structure, more preferably of a multifilament structure, and the cross-sectional area of the sewing thread of the multifilament structure is less than or equal to 0.05mm 2 For example, it may be 0.02mm 2 、0.025mm 2 、0.03mm 2 、0.035mm 2 、0.04mm 2 、0.045mm 2 Or 0.05mm 2 Etc.
In the invention, the sewing thread has a monofilament structure, which means that: adopting single fiber (glass fiber or aramid fiber) as sewing yarn, sewing and fixing the covering film in the space flexible solar cell array; the sewing thread is of a multi-thread structure, which means that: and (3) performing double twisting and braiding on a plurality of fibers (at least one of glass fibers and aramid fibers) to obtain sewing threads, and sewing and fixing the covering film in the space flexible solar cell array by using the sewing threads.
Meanwhile, the invention has no special requirement on the number of fiber filaments in the multi-filament structure obtained by multi-filament braiding, and only the width of the sewing filaments of the multi-filament structure obtained by braiding is required to be smaller than the gap between the battery pieces.
Preferably, the sewing thread is cylindrical or flat, and more preferably flat.
In the invention, the sewing thread is more preferably flat formed by twisting and braiding a plurality of threads, so that the contact area between the sewing thread and the covering film can be increased, and the problem that the covering film is separated from the sewing thread due to too small contact area between the sewing thread and the covering film is avoided.
As a preferable technical scheme of the invention, the sewing thread fixing covering film comprises the following steps: the cover film is sewn with the flexible base film.
The sewing area of the sewing is as follows: gaps between adjacent solar cells in the solar cell array and edge regions of the flexible substrate. Meanwhile, it should be noted that not all the two adjacent solar cells need to be sewn by using sewing threads, and the grid formed by sewing threads can include a plurality of solar cells.
As a preferable technical scheme of the invention, the preparation raw material materials of the flexible substrate comprise polyimide films, glass fibers and epoxy resin.
In the invention, the preparation method of the flexible substrate is not subject to any special limitation, and the preparation method commonly used in the field is applicable.
Preferably, the thickness of the flexible substrate is 0.15mm to 0.25mm, for example, 0.15mm, 0.16mm, 0.17mm, 0.18mm, 0.19mm, 0.20mm, 0.21mm, 0.22mm, 0.23mm, 0.24mm, 0.25mm, or the like may be used.
As a preferable technical scheme of the invention, the solar cell module is obtained by connecting at least two solar cells in series and in parallel.
In the invention, the number of the solar cell sheets is not particularly limited, and the design can be carried out according to practical requirements, and the number of the solar cell sheets can be 2 sheets, 5 sheets, 10 sheets, 20 sheets, 50 sheets, 100 sheets, 150 sheets, 200 sheets or the like. The solar cells are connected in series through the interconnecting piece and are transmitted to the power bus through the bus bar; the interconnecting piece is made of pure silver with the purity of 99.9 percent by stamping and has the thickness of 20 mu m; the bus bar is made of pure silver with a purity of 99.9% by punching, and has a thickness of 50 μm to 75 μm (for example, 50 μm, 52 μm, 55 μm, 57 μm, 60 μm, 63 μm, 66 μm, 68 μm, 72 μm, 75 μm, or the like), and an appropriate thickness of the bus bar can be selected according to the current carrying size. The solar cell series gap is 1.5mm to 2mm (for example, 1.5mm, 1.6mm, 1.7mm, 1.8mm, 1.9mm, 2mm, etc.), and the parallel gap is 1.5mm to 3mm (for example, 1.5mm, 1.8mm, 2mm, 2.2mm, 2.4mm, 2.6mm, 2.8mm, 3mm, etc.).
Meanwhile, in the invention, the covering film is sewn and fixed in the space flexible solar cell array through the sewing threads, and the size of the grid formed by the sewing threads can be adjusted according to the size of the solar cell. In order to ensure the fitting degree and the production efficiency of the encapsulation, the cross section area of the grid formed by the sewing threads is 100-300 cm 2 (e.g., may be 100 cm) 2 、120cm 2 、140cm 2 、160cm 2 、180cm 2 、200cm 2 、220cm 2 、240cm 2 、260cm 2 、280cm 2 Or 300cm 2 And the like), the distance between the sewing needles is 0.6 to 1.2mm (for example, 0.6mm, 0.7mm, 0.8mm, 0.9mm, 1.0mm, 1.1mm or 1.2mm, and the like), and the sewing needle distance is 10 to 30mm (for example, 10mm, 12mm, 14mm, 16mm, 18mm, 20mm, 22mm, 24mm, 26mm, 28mm or 30mm, and the like).
Preferably, the solar cell is a flexible solar cell.
Preferably, the flexible solar cell comprises a three-junction gallium arsenide solar cell, a flexible crystalline silicon solar cell or a flexible CIGS solar cell.
The thickness of the solar cell sheet is preferably not more than 100 μm (for example, 40 μm, 50 μm, 60 μm, 70 μm, 80 μm, 90 μm, 100 μm, or the like), and more preferably not more than 70 μm.
Preferably, the gap between any two adjacent battery pieces is 1.5 mm-2 mm, for example, 1.5mm, 1.6mm, 1.7mm, 1.8mm, 1.9mm or 2mm, etc.
In a preferred embodiment of the present invention, the thickness of the adhesive layer between the flexible substrate and the solar cell module is 0.03mm to 0.05mm, and may be, for example, 0.03mm, 0.032mm, 0.034mm, 0.036mm, 0.038mm, 0.04mm, 0.042mm, 0.044mm, 0.046mm, 0.048mm, 0.05mm, or the like.
As a preferred embodiment of the present invention, the cover film is selected from ETFE film, PTFE film, and transparent polyimide film.
The thickness of the cover film is preferably 0.025mm to 0.125mm, and may be, for example, 0.025mm, 0.03mm, 0.04mm, 0.05mm, 0.06mm, 0.07mm, 0.08mm, 0.09mm, 0.1mm, 0.11mm, 0.12mm, 0.125mm, or the like.
In a second aspect, the present invention provides a method for packaging a space-flexible solar cell array according to the first aspect, the method comprising the steps of:
(1) Coating an adhesive on one side of the flexible substrate to form an adhesive layer;
(2) Placing the solar cell on one side of the adhesive layer, which is far away from the flexible substrate, to form a solar cell module;
(3) And sewing the cover film on one side of the solar cell array far away from the flexible substrate, and sewing gaps between adjacent solar cell sheets and the edge area of the flexible substrate to complete packaging, thereby obtaining the space flexible solar cell array.
In a third aspect, the present invention provides the use of a spatially flexible solar array as described in the first aspect in the field of aerospace.
Compared with the prior art, the invention has the following beneficial effects:
(1) According to the invention, through the design of the space flexible solar cell array structure, the cover film is fixed in the space flexible solar cell array through the use of sewing threads, so that the problems of bubble generation and product reliability reduction caused by the use of packaging adhesive films (or adhesives) and the fixation and sealing of interconnection sheets and bus bars in the assembly in the prior art are effectively solved;
(2) In the space flexible solar cell array provided by the invention, an adhesive layer is not arranged between the solar cell assembly and the cover film, so that the time consumed by curing the adhesive is reduced, and the production efficiency is improved;
(3) The space flexible solar cell array provided by the invention can be partially maintained, and the cost of the space flexible solar cell array is reduced.
Drawings
Fig. 1 is a schematic cross-sectional view of a space flexible solar cell array according to embodiment 1 of the present invention;
fig. 2 is a schematic top view of a space flexible solar cell array according to embodiment 1 of the present invention;
fig. 3 is a schematic cross-sectional structure of a space flexible solar cell array provided in comparative example 1 of the present invention;
the solar cell comprises a 1-flexible substrate, a 2-adhesive layer, a 3-solar cell module, a 31-solar cell piece, a 4-covering film, 5-sewing threads and a 6-adhesive layer.
Detailed Description
The technical scheme of the invention is further described below by the specific embodiments with reference to the accompanying drawings. It will be apparent to those skilled in the art that the examples are merely to aid in understanding the invention and are not to be construed as a specific limitation thereof.
The sources of some of the components used in the following examples and comparative examples are as follows:
glass fiber: europeanism, corning;
aramid fiber: dupont, kevlar, vectran, usa;
ETFE film: dupont, japan, sun-the-sun, the sun-the-earth;
PTFE film: dupont, japan, sun-the-sun, the sun-the-earth;
transparent polyimide film: dupont, kapton, usa.
Example 1
The embodiment provides a space flexible solar cell array and a packaging method thereof, wherein a schematic cross-sectional structure of the space flexible solar cell array is shown in fig. 1, a schematic top view structure of the space flexible solar cell array is shown in fig. 2, and the space flexible solar cell array comprises a flexible substrate 1, an adhesive layer 2, a solar cell module 3 and a covering film 4 which are sequentially overlapped;
the space flexible solar cell array further comprises sewing threads 5, and the sewing threads 5 are used for fixing the covering film 4;
the thickness of the flexible substrate 1 is 0.2mm;
the adhesive layer 2 is prepared from an adhesive (purchased from Shanghai silica gel product research institute) and has a thickness of 0.04mm;
the solar cell module 3 is obtained by connecting 100 three-junction gallium arsenide solar cells 31 in series and in parallel, the thickness of each three-junction gallium arsenide solar cell is 70 mu m, and the gap between any two adjacent three-junction gallium arsenide solar cells 31 is 1.5mm;
the sewing thread 5 is flat and is formed by twisting and braiding a plurality of glass fibers, and the cross section area of the sewing thread is 0.07mm 2 The breaking strength is 1500MPa, the long-term working temperature is more than 300 ℃, and the irradiation resistance is more than 100kRad (Si);
the cover film 4 is selected from ETFE films with a thickness of 0.07mm.
The packaging method of the space flexible solar cell array comprises the following steps:
(1) Coating an adhesive on one side of the flexible substrate 1 to form an adhesive layer 2;
(2) Placing the solar cell 31 on one side of the adhesive layer 2 far away from the flexible substrate 1 to form a solar cell module 3;
(3) And sewing the cover film 4 on one side of the solar cell array far away from the flexible substrate 1, and sewing gaps between adjacent solar cells 31 and the edge area of the flexible substrate 1 to complete packaging, thereby obtaining the space flexible solar cell array.
Example 2
The embodiment provides a space flexible solar cell array and a packaging method thereof, wherein the space flexible solar cell array comprises a flexible substrate, an adhesive layer, a solar cell module and a covering film which are overlapped;
the space flexible solar cell array further comprises sewing threads, wherein the sewing threads are used for fixing the covering film;
the thickness of the flexible substrate is 0.15mm;
the adhesive layer is prepared from an adhesive (purchased from Shanghai silica gel product research institute) and has a thickness of 0.05mm;
the solar cell assembly is obtained by connecting 100 flexible crystalline silicon solar cells in series and in parallel, the thickness of each solar cell is 70 mu m, and the gap between any two adjacent flexible crystalline silicon solar cells is 1.5mm;
the sewing thread is flat and is formed by twisting and braiding a plurality of aramid fibers, and the cross section area is 0.05mm 2 The fracture strength is 3000MPa, the long-term working temperature is more than 150 ℃, and the irradiation resistance is more than 100kRad (Si);
the cover film was selected from PTFE films with a thickness of 0.08mm.
The packaging method of the space flexible solar cell array is the same as that of the embodiment 1.
Example 3
The embodiment provides a space flexible solar cell array and a packaging method thereof, which are different from embodiment 1 in that the sewing thread is a cylindrical and multi-thread structure formed by twisting a plurality of glass fibers, and the cross section area is 0.07mm 2 The strength is 1500MPa, the long-term working temperature is more than 300 ℃, and the irradiation resistance is 100kRad (Si);
other conditions were the same as in example 1.
Comparative example 1
The comparative example provides a space flexible solar cell array and a packaging method thereof, wherein a schematic cross-sectional structure of the space flexible solar cell array is shown in fig. 3, and the space flexible solar cell array is different from the embodiment 1 in that the space flexible solar cell array does not comprise sewing threads 5, and an adhesive layer 6 is arranged between a solar cell module 3 and a cover film 4;
the adhesive layer 6 is prepared from an adhesive (purchased from the institute of science and technology) and has a thickness of 0.04mm;
namely, the space flexible solar cell array comprises a flexible substrate 1, an adhesive layer 2, a solar cell module 3, an adhesive layer 6 and a covering film 4 which are sequentially overlapped.
The packaging method of the space flexible solar cell array comprises the following steps:
the flexible substrate 1, the adhesive layer 2, the solar cell module 3, the adhesive layer 6 and the covering film 4 are sequentially stacked and placed, and then are cured at room temperature for 48 hours to obtain the space flexible solar cell array;
other conditions were the same as in example 1.
The performance of the spatially flexible solar cell arrays provided in examples 1-3 and comparative example 1 were compared:
comparison for improvement in production efficiency: comparing the packaging process of the flexible solar cell array with the size of 1 square meter,
the silicone rubber coating of the flexible substrate with the length of 1 square meter in the comparative example needs 0.5 to 1 hour, the curing needs 24 to 48 hours, and the product needs to stand in the curing process and cannot be subjected to any operation;
in the packaging processes in embodiments 1 to 3, the total length of one square meter to be sewn is smaller than 121 meters, for example, the running speed of 1000 needles/min is adopted, the needle distance is 10mm, the sewing is completed for less than 10.2 minutes, and the packaging processes can be shifted to other production or test procedures without standing after the sewing is completed, so that the production efficiency can be greatly improved by adopting the method.
For reliability improvement:
practice proves that: the interconnection sheet is a point of failure and failure of the space solar cell array, such as is described in ' Cheng Baoyi ' the solar cell array stress relief ring failure analysis and improvement measures [ C ]//2011:4 ] ' or ' Armand S C, liao M H, morris R W.A transient plasticity study and low cycle fatigue analysis of the Space Station Freedom photovoltaic solar array blanket [ C ]//1990MSC World Users Conference.1990 ] ', and avoiding solder, binder coating or spilling onto the interconnection sheet stress relief ring is also an important aspect of the space solar cell array production process. According to the invention, the adhesive layer is not arranged between the solar cell and the cover film, so that the problem that the stress-reducing structures of the interconnection piece and the bus bar are fixedly sealed and cannot exert the stress-reducing effect is avoided, and the reliability of the product is improved.
In summary, the cover film is fixed in the space flexible solar cell array through the sewing threads, so that the problems of air bubble generation and product reliability reduction caused by the fixation and encapsulation of the interconnection sheet and the bus bar in the component due to the use of the packaging adhesive film (or the adhesive) in the prior art are effectively solved; the space flexible solar cell array provided by the invention can be locally maintained, and the maintenance and use cost of the space flexible solar cell array is reduced.
The applicant states that the detailed structural features and detailed process flows of the present invention are described by the above embodiments, but the present invention is not limited to the above detailed structural features and detailed process flows, i.e. it does not mean that the present invention must be implemented depending on the above detailed structural features and detailed process flows. It should be apparent to those skilled in the art that any modification of the present invention, equivalent substitution of selected components, addition of auxiliary components, selection of specific modes, etc. of the present invention, and addition of equivalent substitution of raw materials and auxiliary components, selection of specific modes, etc. of the present invention fall within the scope of protection and disclosure of the present invention.
Claims (16)
1. The space flexible solar cell array is characterized by comprising a flexible substrate, an adhesive layer, a solar cell module, a covering film and sewing threads, wherein the flexible substrate, the adhesive layer, the solar cell module and the covering film are sequentially overlapped;
the solar cell assembly is obtained by connecting at least two solar cells in series or in parallel, gaps exist between the adjacent solar cells, and the gaps between any two adjacent solar cells are 1.5 mm-2 mm;
the sewing area covered by the sewing thread comprises a covering film, an edge area of the flexible substrate and gaps between adjacent solar cells in the solar cell array, so that a plurality of grid structures are formed;
the breaking strength of the sewing thread is more than or equal to 2000 MPa;
the long-term working temperature of the sewing thread is more than or equal to 150 ℃;
the irradiation resistance of the sewing thread is more than or equal to 100kRad (Si).
2. The spatially flexible solar array of claim 1, wherein the sewing filaments are selected from glass fibers and/or aramid fibers.
3. The space flexible solar cell array according to claim 2, wherein the diameters of the glass fiber and the aramid fiber are respectively independent and equal to or more than 25 μm.
4. The spatially flexible solar array of claim 1, wherein the sewing thread is of a monofilament or multifilament construction.
5. The array of claim 4, wherein the sewing thread is a multi-thread structure.
6. The spatial flexible solar array according to claim 1, wherein the flexible substrate is made of a material including polyimide film, glass fiber and epoxy resin.
7. The space flexible solar cell array of claim 1, wherein the thickness of the flexible substrate is 0.15 mm-0.25 mm.
8. The spatially flexible solar array of claim 1, wherein the solar cell is a flexible solar cell.
9. The spatial flexible solar array of claim 8, wherein the flexible solar cell comprises a three junction gallium arsenide solar cell, a flexible crystalline silicon solar cell, or a flexible CIGS solar cell.
10. The spatially flexible solar array of claim 1, wherein the solar cell has a thickness of 100 μm or less.
11. The spatially flexible solar array of claim 10, wherein the solar cell has a thickness of 70 μm or less.
12. The spatial flexible solar cell array according to claim 1, wherein the thickness of the adhesive layer between the flexible substrate and the solar cell module is 0.03mm to 0.05 mm.
13. The spatially flexible solar array of claim 1, wherein the cover film is selected from ETFE film, PTFE film, or transparent polyimide film.
14. The spatially flexible solar array of claim 1, wherein the cover film has a thickness of 0.025 mm~0.125 mm.
15. A method of packaging a spatially flexible solar array according to any one of claims 1 to 14, wherein the method of packaging comprises the steps of:
(1) Coating an adhesive on one side of the flexible substrate to form an adhesive layer;
(2) Placing the solar cell on one side of the adhesive layer, which is far away from the flexible substrate, to form a solar cell module;
(3) And sewing the cover film on one side of the solar cell array far away from the flexible substrate, and sewing gaps between adjacent solar cell modules and the edge area of the flexible substrate to complete packaging, thereby obtaining the space flexible solar cell array.
16. Use of a spatially flexible solar array according to any one of claims 1 to 14 in the field of aerospace.
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| CN207474483U (en) * | 2017-12-12 | 2018-06-08 | 米亚索乐装备集成（福建）有限公司 | Flexible photovoltaic component |
| WO2019196256A1 (en) * | 2018-04-12 | 2019-10-17 | 北京汉能光伏投资有限公司 | Solar cell module, preparation method therefor and vehicle |
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| JP2014053539A (en) * | 2012-09-10 | 2014-03-20 | Toppan Printing Co Ltd | Flexible solar cell module |
| CN106299002A (en) * | 2016-09-14 | 2017-01-04 | 中国电子科技集团公司第四十八研究所 | Flexible solar cell assembly and its preparation method and application |
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