CN106299002B - Flexible solar cell component and its preparation method and application - Google Patents
Flexible solar cell component and its preparation method and application Download PDFInfo
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- CN106299002B CN106299002B CN201610823406.9A CN201610823406A CN106299002B CN 106299002 B CN106299002 B CN 106299002B CN 201610823406 A CN201610823406 A CN 201610823406A CN 106299002 B CN106299002 B CN 106299002B
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- 210000003850 cellular structure Anatomy 0.000 title claims abstract description 46
- 238000002360 preparation method Methods 0.000 title claims abstract description 18
- 238000004806 packaging method and process Methods 0.000 claims abstract description 75
- 210000004027 cell Anatomy 0.000 claims abstract description 71
- 239000002313 adhesive film Substances 0.000 claims abstract description 70
- 238000003475 lamination Methods 0.000 claims abstract description 29
- 229920007790 polymethacrylimide foam Polymers 0.000 claims abstract description 11
- 238000007731 hot pressing Methods 0.000 claims abstract description 10
- 239000010408 film Substances 0.000 claims description 24
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 claims description 23
- 229910052710 silicon Inorganic materials 0.000 claims description 23
- 239000010703 silicon Substances 0.000 claims description 23
- 238000010030 laminating Methods 0.000 claims description 18
- 238000003466 welding Methods 0.000 claims description 16
- 238000005516 engineering process Methods 0.000 claims description 10
- 239000012528 membrane Substances 0.000 claims description 9
- 229920002799 BoPET Polymers 0.000 claims description 8
- 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
- 239000010409 thin film Substances 0.000 claims description 5
- JBRZTFJDHDCESZ-UHFFFAOYSA-N AsGa Chemical compound [As]#[Ga] JBRZTFJDHDCESZ-UHFFFAOYSA-N 0.000 claims description 3
- 229910001218 Gallium arsenide Inorganic materials 0.000 claims description 3
- 229910021417 amorphous silicon Inorganic materials 0.000 claims description 3
- 239000003292 glue Substances 0.000 claims description 3
- 238000001816 cooling Methods 0.000 claims description 2
- 230000006835 compression Effects 0.000 claims 2
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- 238000005452 bending Methods 0.000 abstract description 12
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- 229920006934 PMI Polymers 0.000 description 5
- 230000000694 effects Effects 0.000 description 4
- 238000003892 spreading Methods 0.000 description 4
- 230000007480 spreading Effects 0.000 description 4
- 239000000758 substrate Substances 0.000 description 4
- 239000002253 acid Substances 0.000 description 3
- 230000008602 contraction Effects 0.000 description 3
- 238000002474 experimental method Methods 0.000 description 3
- 150000003949 imides Chemical class 0.000 description 3
- 230000006872 improvement Effects 0.000 description 3
- 238000012536 packaging technology Methods 0.000 description 3
- 235000012431 wafers Nutrition 0.000 description 3
- 150000001875 compounds Chemical class 0.000 description 2
- 230000005611 electricity Effects 0.000 description 2
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- 238000004643 material aging Methods 0.000 description 2
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Classifications
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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
- H01L31/04—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
- H01L31/0481—Encapsulation of modules characterised by the composition of the encapsulation material
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02S—GENERATION OF ELECTRIC POWER BY CONVERSION OF INFRARED RADIATION, VISIBLE LIGHT OR ULTRAVIOLET LIGHT, e.g. USING PHOTOVOLTAIC [PV] MODULES
- H02S30/00—Structural details of PV modules other than those related to light conversion
- H02S30/10—Frame structures
-
- 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
-
- 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
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P70/00—Climate change mitigation technologies in the production process for final industrial or consumer products
- Y02P70/50—Manufacturing or production processes characterised by the final manufactured product
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- Physics & Mathematics (AREA)
- Condensed Matter Physics & Semiconductors (AREA)
- Electromagnetism (AREA)
- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Computer Hardware Design (AREA)
- Microelectronics & Electronic Packaging (AREA)
- Power Engineering (AREA)
- Photovoltaic Devices (AREA)
Abstract
The invention discloses a kind of flexible solar cell component and preparation method and application, the flexible solar cell component includes from top to bottom the upper covering of packaging by hot pressing, the first packaging adhesive film, flexible solar cell array, the second packaging adhesive film, support member, the 3rd packaging adhesive film and lower covering successively, and the support member is polymethacrylimide foam plate.The preparation method comprises the following steps：First press and carry out lamination from top to bottom for the order of upper covering, the first packaging adhesive film, flexible solar cell array, the second packaging adhesive film, support member, the 3rd packaging adhesive film and lower covering, then be laminated.The flexible solar cell component has advantages below：Surface density is low, bending and flexility are good, adapt to the fitting of airfoil camber, good reliability, in the absence of the encapsulation problem such as warpage, fragmentation；There is wide application on the spacecrafts such as solar energy unmanned plane.
Description
Technical field
The invention belongs to technical field of solar batteries, more particularly to a kind of space flexible solar cell component and its system
Preparation Method and application.
Background technology
HAE solar energy unmanned plane have flying height height, longevity of service, overlay area it is wide, using flexibly,
Operating cost is low and the advantages of non-environmental-pollution, as performing information, scoutings, monitor and the task such as communication relay desired air
Platform, there is boundless application prospect.It can be as power in HAE non-stop flight by the use of solar radiation
Unmanned vehicle, it is converted solar energy into electrical energy using photocell, is driven propeller rotation to produce by motor and is flown
Action edge.Daytime, the solar cell that solar energy unmanned plane is laid by body surface can be converted to the solar radiation of absorption
Electric energy, maintains the operation of dynamical system, avionic device and payload, while being charged to airborne secondary power supply.If white
The need for the ability of its storage disclosure satisfy that night flying, then solar energy unmanned plane can realize " permanent " flight in theory.
In order to ensure that solar powered aircraft has enough flying powers, generally require to lay on its wing, fuselage more
Solar cell module, mounting process of the solar cell on solar powered aircraft is technological difficulties.At present, on unmanned plane
The solar cell of laying is mostly rigid solar cell, due to being limited by solar energy Unmanned Aerial Vehicle Airfoil radian and mounting structure
System, the rigid and frangible solar battery array plane easily split is difficult to adapt to the laminating and installation at the big position of Curvature varying on wing.When
When wing stand under load is deformed, battery may be badly damaged.This requires that the encapsulation to solar cell, solar energy should be solved the problems, such as
Aircraft provides good laying platform for battery again in itself.To ensure pneumatic efficiency, solar cell will not only ensure to install
When it is conformal with aircraft skin, and to ensure to be brought into close contact with covering in the whole flight course, so solar cell
Pliability is most important.Traditional rigid solar cell module typically uses PET light-transmissive films（About 200 μ m-thicks）+ EVA layer（About
500 μ m-thicks）+ monocrystalline silicon piece or polysilicon chip（About 180 μ m-thicks）+ TPE backlights, its surface density is usually 2.0~2.5 kg/
m2, cause solar cell module to lack pliability, do not simply fail to adapt to fit with airfoil camber, and quality itself compared with
Greatly, the load of solar powered aircraft is reduced, it is difficult to meet the application demand of solar powered aircraft.
Solar cell array after being thinned has certain bending property, is referred to as flexible solar cell component.But battery
Piece is not more Bao Yuehao, because the fragility of cell piece increases after being thinned, it is easily broken in the case where flexural loading is uneven
Split, be particularly more easy to fragmentation in the similar application for having large curved structure such as solar energy unmanned plane.Thus conventional flexibility is too
Positive battery component still has very big rigidity, causes after bending that screen resilience is larger, it is difficult to be fixed in the songs such as unmanned plane wing
The big body structure surface of rate.Therefore, conventional flexible solar cell component is in the big body structure surface of unmanned plane wing skeleton iso-curvature
It is upper to install in laying, solar module and wing skeleton etc. are carried out mainly by mechanical structures such as increase rivet, pin, hasps
It is locked.So, the weight of solar energy unmanned plane etc. is not only increased, and these mechanical fixed structures destroy wing etc.
Surface flatness and unmanned plane etc. pneumatic conformal performance.
For example, in the solar module manufacturing technology of disclosed solar energy unmanned plane, such as CN
Solar module is prepared using rigid solar cell in 203659894 U and CN201510680597, in order to ensure electricity
Rigid solar cell is not chipping in BENDING PROCESS in the component of pond, and component can not carry out big flexural deformation, it is difficult to adapt to
The laminating at the big position of Curvature varying on wing.Though in addition, such as more traditional solar module face in the U patents of CN 203659894
Density mitigates more than 35%, and surface density still reaches 1.2Kg/m2More than；Meanwhile, the solar module prepared in the patent lacks
Flexible support substrate is difficult to ensure that solar module and unmanned plane wing skeleton general character effect and solar cell piece are reliable
Property.Equally, although heat-barrier material flexible in CN201510680597 patents is as support substrate, due to the modular construction and
Technique, it is difficult to avoid component warpage that different materials are caused through overheat contraction after unbalanced and the rigid solar cell of component internal can
The problems such as by property difference.
The content of the invention
The technical problem to be solved in the present invention be overcome the deficiencies in the prior art there is provided a kind of surface density it is low, bending and it is soft
Tough performance is good, adapt to encapsulate the flexible sun of problem with the fitting of airfoil camber, good reliability, in the absence of warpage, fragmentation etc.
Battery component, correspondingly provides a kind of preparation method of flexible solar cell component and its flies in spaces such as solar energy unmanned planes
Application on row device.
In order to solve the above technical problems, the present invention uses following technical scheme：
A kind of flexible solar cell component, including the upper covering of packaging by hot pressing, the first packaging adhesive film, soft successively from top to bottom
Property solar battery array, the second packaging adhesive film, support member, the 3rd packaging adhesive film and lower covering, the support member be polymethyl
Acid imide foam plate.
A kind of flexible solar cell component, including the upper covering of packaging by hot pressing, the first packaging adhesive film, soft successively from top to bottom
Property solar battery array, the second packaging adhesive film, lower covering, the 3rd packaging adhesive film and support member, the support member be polymethyl
Acid imide foam plate.
It is used as the further improvement of above-mentioned two technical scheme：
The thickness of the polymethacrylimide foam plate be 0.2mm~3mm, 30 Kg/m3 of density~100Kg/m3,
Compressive strength 0.3MPa~7.5MPa, modulus of compressibility 20MPa~200MPa, tensile strength 0.8MPa~8MPa, stretch modulus
40MPa~400MPa, torsional shear strength 0.4MPa~7MPa, torsional shear modulus 10MPa~200MPa.
The flexible solar cell array includes multiple solar cell pieces and photovoltaic welding belt, and adjacent solar cell piece passes through described
Photovoltaic welding belt is connected.
The thickness of the solar cell piece is 50 μm~140 μm, the gap between adjacent solar cell piece for 0.1mm~
1mm, the thickness of the photovoltaic welding belt is 0.03mm~0.3mm.
It is thin that the solar cell piece includes flexible crystal silicon solar battery piece, thin film gallium arsenide solar cell piece, CIGS
Film solar cell piece or amorphous silicon film solar battery piece.
The upper covering includes PET film, ETFE films, PVC film or PTFE film, and the thickness of the upper covering is 20 μm~50 μ
M, transmitance is 80%~100%；The lower covering includes PET film, ETFE films, PVC film or PTFE film, the thickness of the lower covering
For 20 μm~50 μm.
First packaging adhesive film is POE glued membranes or EVA adhesive film, and the thickness of first packaging adhesive film is 50 μm~150 μ
m；Second packaging adhesive film is POE glued membranes or EVA adhesive film, and the thickness of second packaging adhesive film is 50 μm~150 μm；It is described
3rd packaging adhesive film is POE glued membranes or EVA adhesive film, and the thickness of the 3rd packaging adhesive film is 50 μm~150 μm.
As a total inventive concept, the present invention also provides a kind of preparation method of flexible solar cell component, including
Following steps：First press from top to bottom as upper covering, the first packaging adhesive film, flexible solar cell array, the second packaging adhesive film, support
The order of part, the 3rd packaging adhesive film and lower covering carries out lamination, then is laminated, and laminating temperature is 80 DEG C~150 DEG C, lamination pressure
Power is 15 kPa~100kPa, and lamination times are 5min~30min.
As a total inventive concept, the present invention also provides a kind of preparation method of flexible solar cell component, including
Following steps：First press is upper covering, the first packaging adhesive film, flexible solar cell array, the second packaging adhesive film and lower illiteracy from top to bottom
The order of skin is carried out after lamination, carries out first step laminating technology, and laminating temperature is 80 DEG C~150 DEG C, and lamination pressure is 15 kPa
~100kPa, lamination times are 5min~30min；Cooling, obtains intermediate module, then by being intermediate module, the 3rd from top to bottom
Packaging adhesive film, the order of support member carry out lamination second step laminating technology, and laminating temperature is 50 DEG C~120 DEG C, and lamination pressure is
10 kPa~50kPa, lamination times are 5min~20min.
As a total inventive concept, the present invention also provides a kind of above-mentioned flexible solar cell component or above-mentioned soft
Flexible solar cell component prepared by the preparation method of property solar module is in the carry-on application of space solar.
Space solar aircraft includes solar energy unmanned plane, solar energy dirigible, solar energy aerostat etc..
Compared with prior art, the advantage of the invention is that：
If the 1, flexible solar cell component is rigidly too high, the bending effect of solar module is difficult to meet greater curvature
Application demand；Although the solar cell array bending property increase after being thinned, fragility is consequently increased, uneven in flexural loading
Easily fragmentation in the case of even, is particularly more easy to fragmentation in the similar application for having large curved structure such as solar energy unmanned plane.
If wanting easily to lay solar module on this surface for having large curved structure, only way is thinned as much as possible
While solar cell piece, the package quality of flexible solar cell component is improved, thus the requirement of its packaging protection is than commonly soft
Property solar module is higher.I.e. in order to ensure that component both has good pliability and bendability, and in BENDING PROCESS not
It is destroyed, it is desirable to which that encapsulating material and packaging technology are improved, reach the flexibility and rigidity of the solar module after encapsulation
To optimum balance, optimal spreading property is obtained.Wherein, the selection of the support member in solar module is particularly critical, is whole
Whether individual solar module has the most crucial part of optimal spreading property.
Selection of the applicant to encapsulating material and packaging technology has carried out substantial amounts of experimental exploration, in these heuristic process
In, seem pliability and the suitable material of rigidity it has been found that a large amount of, such as certain thickness high strength fibre cloth and its compound
The hollow type such as substrate, honeycomb compound substrate, certain thickness TPE backboards, certain thickness metallic plate etc., are assembled into soft as support member
After property solar module, during being layed on the surface of the large curved structure such as wing, otherwise protective value difference is led
Cell piece fragmentation is caused, otherwise screen resilience is larger after battery component bending, it is impossible to come in curved-surface structure surface spreading.In addition,
During packaging technology is explored, it has been found that due to each material percent thermal shrinkage difference in battery component, support member selection is improper, warp
Cross after packaging by hot pressing, warping phenomenon often occurs in flexible solar cell component, cause reliability to become poor.Thus, support member
Also require to match with the other materials such as percent thermal shrinkage such as covering, packaging plastic as far as possible.
The flexible solar cell component of the present invention, applicant attempts by substantial amounts of experiment, final preferably polymethyl
Acid imide foam plate is as the support member of flexible solar cell component, and experiment shows, warping phenomenon is not present in encapsulation process, and
And the flexible solar cell component after encapsulation has optimal pliability, can carry out big flexural deformation, flexibility is can guarantee that again
Thinned solar cell piece BENDING PROCESS in component is not destroyed, i.e., with extraordinary spreading property, this flexible sun electricity
Pond component, only by gluing with regard to that can be fixed on the surface of the warp architectures such as unmanned plane wing, can not only simplify solar module
Laying the installation procedure on carrier, and installing fixed weight greatly reduces, and can lift the surfaces such as wing skeleton and illiteracy
The pneumatic safety effect of skin, in a word, greatly improved the load-carrying ability and flying quality of the spacecrafts such as solar energy unmanned plane.
In addition, the position setting of support member is improper also to have component warpage and component internal fragility solar cell reliability
Poor the problems such as.Applicant after experiment by having found, the polymethyl acyl that flexible solar cell array is positioned over into lightweight flexible is sub-
Amine（PMI）Above foam sheet, flexible upper covering and lower covering are respectively positioned at the outmost surface of battery component, this integration
The flexible crystal silicon solar battery component prepared further avoid through the unbalanced component warpage caused of overheat contraction and component
The problems such as internal fragility solar cell poor reliability.
2nd, further, the thickness of polymethacrylimide foam plate is 0.2mm~3mm, the Kg/m of density 303~
100Kg/m3, compressive strength 0.3MPa~7.5MPa, modulus of compressibility 20MPa~200MPa, tensile strength 0.8MPa~8MPa, drawing
Modulus 40MPa~400MPa, torsional shear strength 0.4MPa~7MPa, torsional shear modulus 10MPa~200MPa are stretched, passes through limit
Determine these parameters of PMI thin plates, can be further assured that flexible solar cell component obtains optimal pliability, meet unmanned plane machine
Wing application demand.
3rd, further, in flexible solar cell array, the thickness of solar cell piece is 50 μm~140 μm, it is this it is ultra-thin too
Positive cell piece can be by prepared by wafer thinning technique and ultra thin silicon wafers preparation technology.Gap between adjacent solar cell piece
For 0.1mm~1mm, use thickness to connect adjacent solar cell piece for 0.03mm~0.3mm ultra-thin welding, constitute soft
Property solar battery array.The flexible crystal silicon solar component surface density of development is greatly reduced 80% compared to conventional solar cell component
More than, weight is greatly reduced, so that the load-carrying ability of the spacecrafts such as solar energy unmanned plane greatly improved.
Brief description of the drawings
Fig. 1 is the structural representation of the flexible solar cell component of the embodiment of the present invention 1.
Fig. 2 is applied to the knot of certain model solar energy unmanned plane wing for the flexible solar cell component of the embodiment of the present invention 1
Structure schematic diagram.
Fig. 3 is the structural representation of the flexible solar cell component of the embodiment of the present invention 2.
Label declaration：1st, upper covering；21st, the first packaging adhesive film；3rd, crystal silicon solar battery piece；22nd, the second packaging adhesive film；
4th, photovoltaic welding belt；5th, Polymethacrylimide（PMI）Foam sheet；23rd, the 3rd packaging adhesive film；6th, lower covering.
Embodiment
Below in conjunction with Figure of description and specific preferred embodiment, the invention will be further described, but not therefore and
Limit the scope of the invention.
Embodiment 1：
As shown in figure 1, a kind of flexible solar cell component of the invention, including the upper illiteracy of packaging by hot pressing successively from top to bottom
Skin 1, the first packaging adhesive film 21, flexible solar cell array, the second packaging adhesive film 22, support member, the 3rd packaging adhesive film 23 and lower illiteracy
Skin 6, the support member is polymethacrylimide foam plate 5.
The thickness of polymethacrylimide foam plate 5 is preferably 0.5mm~3mm, and density is preferably 30 Kg/m3~
100Kg/m3, compressive strength 0.3MPa~7.5MPa, modulus of compressibility 20MPa~200MPa, tensile strength 0.8MPa~8MPa are drawn
Stretch modulus 40MPa~400MPa, torsional shear strength 0.4MPa~7MPa, torsional shear modulus 10MPa~200MPa.
In the present embodiment, the thickness of polymethacrylimide foam plate 5 is 0.5mm, the Kg/m of density 503~100Kg/
m3, compressive strength 1.0MPa, modulus of compressibility 44MPa, tensile strength 1.7MPa, stretch modulus 74MPa, torsional shear strength
0.92MPa, torsional shear modulus 23MPa.
In the present embodiment, flexible solar cell array includes multiple crystal silicon solar battery pieces 3 and photovoltaic welding belt 4, adjacent crystal silicon
Solar cell piece 3 is connected by photovoltaic welding belt 4, finally constitutes flexible solar cell array.
The thickness of crystal silicon solar battery piece 3 is preferably 50 μm~140 μm, the gap between adjacent crystal silicon solar battery piece 3
Preferably 0.1mm~1mm, thickness is preferably 0.03mm~0.3mm.
In the present embodiment, the thickness of crystal silicon solar battery piece 3 is the gap between 100 μm, adjacent crystal silicon solar battery piece 3
For 0.5mm, the thickness of photovoltaic welding belt 4 is 0.08mm.
The flexible solar cell array of the present embodiment, crucial preparation flow is as follows：（1）Pass through wafer thinning technique and ultra-thin silicon
Piece preparation technology prepares multiple crystal silicon solar battery pieces 3 that thickness is 100 microns, this ultra-thin crystal silicon solar battery piece 3
Possesses certain flexibility, single crystal silicon solar battery chip size size is 40mm × 156mm；（2）Thickness is used for 0.08mm's
Ultra-thin welding 4, by crystal silicon solar battery welding procedure, by adjacent crystal silicon solar battery piece 3（Adjacent crystal silicon solar battery piece
Gap between 3 is 0.5mm）Interconnection, ultimately forms flexible solar cell array.
In other examples, flexible crystal silicon solar battery piece can also replace with thin film gallium arsenide solar cell piece,
CIGS thin-film solar cell piece or amorphous silicon film solar battery piece.
In the present embodiment, upper covering 1 is PET film, and thickness is 25 μm, transmitance is 95%.In other embodiments, it is upper to cover
Skin 1 or ETFE films, PVC film or PTFE film, the thickness of upper covering 1 is preferably 20 μm~50 μm.
In the present embodiment, the first packaging adhesive film 21, the second packaging adhesive film 22 and the 3rd packaging adhesive film 23 are POE glued membranes,
Thickness is 75 μm.In other embodiments, EVA adhesive film also may be selected in each packaging adhesive film, and the thickness of each packaging adhesive film is preferably
50 μm~150 μm.
In the present embodiment, lower covering 6 is PET film, and thickness is 25 μm.In other embodiments, lower covering 6 or ETFE
Film, PVC film or PTFE film, the thickness of lower covering 6 is preferably 20 μm~50 μm.
A kind of preparation method of flexible solar cell component of the invention, comprises the following steps：First by from top to bottom to be upper
Covering 1, the first packaging adhesive film 21, flexible solar cell array, the second packaging adhesive film 22, Polymethacrylimide（PMI）Foam
The order of thin plate 5, the 3rd packaging adhesive film 23 and lower covering 6 carries out lamination, is subsequently placed into laminating machine and is heated, be laminated, plus
Hot temperature is 130 DEG C, and lamination pressure is 80kPa, and the heat time is 10min.Flexible solar cell array is positioned over lightweight flexible
Polymethacrylimide（PMI）Above foam sheet, flexible upper covering and lower covering are located at battery component most respectively
Thermal contraction is harmonious preferably in outer surface, this structure design, hot pressing, using better simply step laminating, you can system
Standby non-assembly warpage, the flexible solar cell component of battery good reliability.Made solar energy unmanned plane out uses flexibility too
The surface density of positive battery component is only 0.48 kg/m2, compared to the lamination scheme with traditional solar cell module, its face is close
Degree reduces more than 80%.
As shown in Fig. 2 the flexible solar cell component of the present embodiment is installed on certain model solar energy unmanned plane wing,
The both sides of upper covering 1 are moderately extended compared with miscellaneous part in battery component preparation process, and in advance in wing skeleton upper surface
Middle part processes a groove, and part of the upper covering below 1 is positioned over into viscose glue in groove and fixed, the prolongation of upper covering 1 then glues
Be connected to unmanned plane wing skeleton surface, practice have shown that, due to the present invention flexible solar cell component have certain pliability and
Cell piece protection is good non-breakable in bending property, and BENDING PROCESS, the flexible solar cell component can perfection be fitted in
In the groove of wing skeleton.This structure greatly improves the conformal effect and surface light of solar cell module and wing skeleton
Slippery, greatly improved the flight aeroperformance and reliability of solar energy unmanned plane.Also, with it is conventional by rivet, pin, take
The mechanical structures such as button compared with the manufacture assembly method that wing skeleton is locked, enormously simplify solar module
Solar cell module and is installed fixed weight and greatly reduced in the mounting process of solar energy unmanned plane, so as to greatly improve
The load-carrying ability of solar energy unmanned plane.
Embodiment 2：
As shown in figure 3, a kind of flexible solar cell component of the invention, including the upper illiteracy of packaging by hot pressing successively from top to bottom
Skin 1, the first packaging adhesive film 21, flexible solar cell array, the second packaging adhesive film 22, lower covering 6, the 3rd packaging adhesive film 23 and support
Part, the support member is polymethacrylimide foam plate 5.
In the present embodiment, the thickness of polymethacrylimide foam plate 5 is 0.5mm, the Kg/m of density 503~100Kg/
m3, compressive strength 32MPa, modulus of compressibility 0.44MPa, tensile strength 23MPa, stretch modulus 0.88MPa, torsional shear strength
0.48MPa, torsional shear modulus 13MPa.
In the present embodiment, flexible solar cell array includes multiple crystal silicon solar battery pieces 3 and photovoltaic welding belt 4, adjacent crystal silicon
Solar cell piece 3 is connected by photovoltaic welding belt 4, finally constitutes flexible solar cell array.
In the present embodiment, the thickness of crystal silicon solar battery piece 3 is the gap between 100 μm, adjacent crystal silicon solar battery piece 3
For 0.5mm, the thickness of photovoltaic welding belt 4 is 0.08mm.
In the present embodiment, upper covering 1 is PET film, and thickness is 25 μm, transmitance is 95%.
In the present embodiment, the first packaging adhesive film 21, the second packaging adhesive film 22 and the 3rd packaging adhesive film 23 are POE glued membranes,
Thickness is 75 μm.
In the present embodiment, lower covering 6 is PET film, and thickness is 25 μm.
A kind of preparation method of flexible solar cell component of the invention, comprises the following steps：First by from top to bottom to be upper
After covering 1, the first packaging adhesive film 21, flexible solar cell array, the order lamination of the second packaging adhesive film 22 and lower covering 6, carry out
First step laminating technology, laminating temperature is 130 DEG C, and lamination pressure is 80kPa, and lamination times are 10min；Then, treat that it is cooled down
To room temperature, by the order lamination for being from top to bottom component, the 3rd packaging adhesive film 23, support member that the first step is laminated acquisition, enter
Row second step laminating technology, laminating temperature is 80 DEG C, and lamination pressure is 40kPa, and lamination times are 8min.Applicant it is flexible too
Found during the positive step packaging by hot pressing of battery component one, polymethacrylimide foam plate 5 is placed in the bottom of battery component,
Because each material percent thermal shrinkage is different in component, battery component is caused to there is slight warpage, reliability becomes poor.Pass through two steps layer
Pressure technique, releasably due to component warping phenomenon that material percent thermal shrinkage difference is caused.
Made solar energy unmanned plane out is only 0.48 kg/m with the surface density of flexible solar cell component2, compare
With the lamination scheme of traditional solar cell module, its surface density reduces more than 80%.
The above is only the preferred embodiment of the present invention, and protection scope of the present invention is not limited merely to above-mentioned implementation
Example.All technical schemes belonged under thinking of the present invention belong to protection scope of the present invention.It is noted that for the art
Those of ordinary skill for, improvements and modifications under the premise without departing from the principles of the invention, these improvements and modifications also should
It is considered as protection scope of the present invention.
Claims (10)
1. a kind of flexible solar cell component, including the upper covering of packaging by hot pressing, the first packaging adhesive film, flexibility successively from top to bottom
Solar battery array, the second packaging adhesive film, support member, the 3rd packaging adhesive film and lower covering, it is characterised in that the support member is poly-
Methacrylimide cystosepiment；
The thickness of the polymethacrylimide foam plate is 0.2mm~3mm, the Kg/m of density 303~100Kg/m3, compression is by force
Degree 0.3MPa~7.5MPa, modulus of compressibility 20MPa~200MPa, tensile strength 0.8MPa~8MPa, stretch modulus 40MPa~
400MPa, torsional shear strength 0.4MPa~7MPa, torsional shear modulus 10MPa~200MPa.
2. a kind of flexible solar cell component, including the upper covering of packaging by hot pressing, the first packaging adhesive film, flexibility successively from top to bottom
Solar battery array, the second packaging adhesive film, lower covering, the 3rd packaging adhesive film and support member, it is characterised in that the support member is poly-
Methacrylimide cystosepiment；
The thickness of the polymethacrylimide foam plate is 0.2mm~3mm, the Kg/m of density 303~100Kg/m3, compression is by force
Degree 0.3MPa~7.5MPa, modulus of compressibility 20MPa~200MPa, tensile strength 0.8MPa~8MPa, stretch modulus 40MPa~
400MPa, torsional shear strength 0.4MPa~7MPa, torsional shear modulus 10MPa~200MPa.
3. flexible solar cell component according to claim 1 or 2, it is characterised in that the flexible solar cell array bag
Multiple solar cell pieces and photovoltaic welding belt are included, adjacent solar cell piece is connected by the photovoltaic welding belt.
4. flexible solar cell component according to claim 3, it is characterised in that the thickness of the solar cell piece is 50
μm~140 μm, the gap between adjacent solar cell piece is 0.1mm~1mm, the thickness of the photovoltaic welding belt for 0.03mm~
0.3mm。
5. flexible solar cell component according to claim 4, it is characterised in that the solar cell piece includes flexible brilliant
Silicon solar cell piece, thin film gallium arsenide solar cell piece, CIGS thin-film solar cell piece or amorphous silicon film solar battery
Piece.
6. the flexible solar cell component according to claim 4 or 5, it is characterised in that the upper covering include PET film,
ETFE films, PVC film or PTFE film, the thickness of the upper covering is 20 μm~50 μm, and transmitance is 80%~100%；The lower illiteracy
Skin includes PET film, ETFE films, PVC film or PTFE film, and the thickness of the lower covering is 20 μm~50 μm.
7. the flexible solar cell component according to claim 4 or 5, it is characterised in that first packaging adhesive film is POE
Glued membrane or EVA adhesive film, the thickness of first packaging adhesive film is 50 μm~150 μm；Second packaging adhesive film be POE glued membranes or
EVA adhesive film, the thickness of second packaging adhesive film is 50 μm~150 μm；3rd packaging adhesive film is POE glued membranes or EVA glue
Film, the thickness of the 3rd packaging adhesive film is 50 μm~150 μm.
8. the preparation method of the flexible solar cell component as described in claim 1,3~7 any one, it is characterised in that including
Following steps：First press from top to bottom as upper covering, the first packaging adhesive film, flexible solar cell array, the second packaging adhesive film, support
The order of part, the 3rd packaging adhesive film and lower covering carries out lamination, then is laminated, and laminating temperature is 80 DEG C~150 DEG C, lamination pressure
Power is 15 kPa~100kPa, and lamination times are 5min~30min.
9. the preparation method of the flexible solar cell component as described in any one of claim 2~7, it is characterised in that including with
Lower step：First press is upper covering, the first packaging adhesive film, flexible solar cell array, the second packaging adhesive film and lower covering from top to bottom
Order lamination after, carry out first step laminating technology, laminating temperature be 80 DEG C~150 DEG C, lamination pressure be 15 kPa~
100kPa, lamination times are 5min~30min；Cooling, obtains intermediate module, then by being intermediate module, the 3rd envelope from top to bottom
Glued membrane, the order lamination of support member are filled, second step laminating technology is carried out, laminating temperature is 50 DEG C~120 DEG C, and lamination pressure is 10
KPa~50kPa, lamination times are 5min~20min.
10. flexible solar cell component or flexibility as claimed in claim 8 or 9 as described in any one of claim 1~7 are too
Flexible solar cell component prepared by the preparation method of positive battery component is in the carry-on application of space solar.
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| JP6904795B2 (en) * | 2017-06-09 | 2021-07-21 | トヨタ自動車株式会社 | Solar cell module and its manufacturing method |
| DE102018209112A1 (en) * | 2018-06-08 | 2019-12-12 | Audi Ag | Photovoltaically active laminate |
| CN109686815B (en) * | 2018-11-15 | 2021-10-15 | 上海空间电源研究所 | Manufacturing method for positioning and upper plate pasting of flexible array solar cell module for space |
| CN112216753B (en) * | 2020-09-17 | 2022-08-02 | 中国电子科技集团公司第十八研究所 | Flexible thin film solar cell module for near space aircraft and preparation method |
| CN112382685A (en) * | 2020-11-02 | 2021-02-19 | 中国科学院上海微系统与信息技术研究所 | Double-sided ultrathin silicon-based heterojunction solar cell flexible photovoltaic module and preparation method thereof |
| CN112599624A (en) * | 2020-12-15 | 2021-04-02 | 贵州梅岭电源有限公司 | Body-mounted integrated flexible solar cell array and preparation method thereof |
| CN115149217B (en) * | 2021-03-30 | 2023-11-14 | 京东方科技集团股份有限公司 | Flexible electrode, display device and wearable equipment |
| CN113178501A (en) * | 2021-04-06 | 2021-07-27 | 中国科学院上海微系统与信息技术研究所 | Flexible photovoltaic module and preparation method thereof |
| CN113270511A (en) * | 2021-04-29 | 2021-08-17 | 中国电子科技集团公司第十八研究所 | Photovoltaic and energy storage battery composite structure and preparation method thereof |
| FR3126810A1 (en) | 2021-09-07 | 2023-03-10 | Commissariat à l'énergie atomique et aux énergies alternatives | Flexible photovoltaic module |
| CN115832089B (en) * | 2022-12-29 | 2024-02-02 | 苏州馥昶空间技术有限公司 | Space flexible solar cell array and packaging method and application thereof |
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