CN107039561A - The preparation method of the ultralight solar cell substrate of composite - Google Patents
The preparation method of the ultralight solar cell substrate of composite Download PDFInfo
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- CN107039561A CN107039561A CN201710350246.5A CN201710350246A CN107039561A CN 107039561 A CN107039561 A CN 107039561A CN 201710350246 A CN201710350246 A CN 201710350246A CN 107039561 A CN107039561 A CN 107039561A
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- solar cell
- cell substrate
- reinforcement
- ultralight
- edge strip
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- 239000000758 substrate Substances 0.000 title claims abstract description 66
- 239000002131 composite material Substances 0.000 title claims abstract description 17
- 238000002360 preparation method Methods 0.000 title claims abstract description 10
- 230000002787 reinforcement Effects 0.000 claims abstract description 37
- 239000004744 fabric Substances 0.000 claims abstract description 15
- 239000003822 epoxy resin Substances 0.000 claims abstract description 13
- 229920000647 polyepoxide Polymers 0.000 claims abstract description 13
- 229920006231 aramid fiber Polymers 0.000 claims abstract description 10
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 9
- 229910052799 carbon Inorganic materials 0.000 claims abstract description 9
- 239000000835 fiber Substances 0.000 claims abstract description 9
- 239000012528 membrane Substances 0.000 claims abstract description 9
- 238000013461 design Methods 0.000 claims abstract description 6
- 238000003754 machining Methods 0.000 claims abstract description 4
- 229920000515 polycarbonate Polymers 0.000 claims abstract description 4
- 239000011521 glass Substances 0.000 claims description 11
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 9
- 239000004917 carbon fiber Substances 0.000 claims description 9
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 9
- 239000003292 glue Substances 0.000 claims description 7
- 238000012545 processing Methods 0.000 claims description 6
- 238000010438 heat treatment Methods 0.000 claims description 5
- 238000005253 cladding Methods 0.000 claims description 3
- 150000001875 compounds Chemical class 0.000 claims description 3
- 238000001816 cooling Methods 0.000 claims description 3
- 239000004425 Makrolon Substances 0.000 claims 1
- 239000000463 material Substances 0.000 claims 1
- 238000000034 method Methods 0.000 abstract description 17
- 239000005437 stratosphere Substances 0.000 abstract description 7
- 239000000047 product Substances 0.000 abstract description 5
- 239000004417 polycarbonate Substances 0.000 abstract description 3
- 239000012467 final product Substances 0.000 abstract description 2
- 239000000123 paper Substances 0.000 description 7
- 238000005516 engineering process Methods 0.000 description 6
- 238000007711 solidification Methods 0.000 description 5
- 230000008023 solidification Effects 0.000 description 5
- 238000010276 construction Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 239000011347 resin Substances 0.000 description 3
- 229920005989 resin Polymers 0.000 description 3
- 238000000465 moulding Methods 0.000 description 2
- 210000003205 muscle Anatomy 0.000 description 2
- 241001466460 Alveolata Species 0.000 description 1
- 239000004760 aramid Substances 0.000 description 1
- 229920003235 aromatic polyamide Polymers 0.000 description 1
- 238000009954 braiding Methods 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 150000002148 esters Chemical class 0.000 description 1
- 238000007731 hot pressing Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229920003229 poly(methyl methacrylate) Polymers 0.000 description 1
- 239000004926 polymethyl methacrylate Substances 0.000 description 1
- 239000002994 raw material Substances 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
Classifications
-
- 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
- H01L31/04—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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Condensed Matter Physics & Semiconductors (AREA)
- Electromagnetism (AREA)
- General Physics & Mathematics (AREA)
- Computer Hardware Design (AREA)
- Microelectronics & Electronic Packaging (AREA)
- Power Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Photovoltaic Devices (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
The invention belongs to the preparation method of stratosphere flight device technical field, more particularly to a kind of ultralight solar cell substrate of composite.It includes the design requirement according to solar cell substrate, makes edge strip reinforcement, and edge strip reinforcement includes long side reinforcement, short side reinforcement and fillet reinforcement；Required according to the laying of solar cell substrate, prepare carbon fibre initial rinse fabric；According to solar cell substrate requirement in the pre-buried fixedly connected part in aramid fiber paper honeycomb relevant position, connector is that polycarbonate plate is obtained by machining；Epoxy resin glued membrane is plated in the aramid fiber paper honeycomb upper and lower surface of pre-buried completion.The advantage of the invention is that providing a kind of new method for the solar cell substrate making of stratosphere flight device, technique is relatively easy, and preferably, product intensity is higher, lightweight, and producing efficiency is higher for final product quality.
Description
Technical field
The invention belongs to stratosphere flight device technical field, more particularly to a kind of ultralight solar cell substrate of composite
Preparation method.
Background technology
In recent years, each state is all in all kinds of stratosphere aircraft that conduct a research.Stratospheric airship is a kind of novel low-cost, low
Energy consumption stratosphere flight device, its solar array serves key effect in terms of energy control turns into key technology,
General solar cell substrate all differs nearly 1 times with ultralight solar cell substrate using carbon fiber board or its intensity of glass substrate
As many as, there is sandwich structure and answer in 3 times nearlyer than ultralight solar cell substrate weight again of solar cell substrate in equality strength
The appearance for the problems such as closing layering, bonding bubble is, it is necessary to study a kind of lightweight, the ultralight solar cell substrate of efficient composite
Solve above-mentioned bottleneck problem.
The content of the invention
The technical problem to be solved in the present invention is how to overcome the deficiencies in the prior art, proposes that a kind of composite is ultralight too
The preparation method of positive energy cell substrates, makes the ultralight solar cell substrate of composite.
The technical scheme that uses to achieve the above object of the present invention is：The making of the ultralight solar cell substrate of composite
Method, including following price step：
Step one：According to the design requirement of solar cell substrate, edge strip reinforcement is made, edge strip reinforcement includes long side
Reinforcement, short side reinforcement and fillet reinforcement；Reinforcement is obtained using the molding of 3K carbon fibre initial rinse fabrics；
Step 2：Required according to the laying of solar cell substrate, prepare carbon fibre initial rinse fabric；
Step 3：According to solar cell substrate requirement in the pre-buried fixedly connected part in aramid fiber paper honeycomb relevant position, connection
Part is that polycarbonate plate is obtained by machining；
Step 4：Epoxy resin glued membrane is plated in the aramid fiber paper honeycomb upper and lower surface of pre-buried completion；
Step 5：The 1K carbon fiber twill weave cloth of primary load bearing layer is plated according to solar cell substrate laying；
Step 6：Glass mold is fixed in the compound solar cell substrate preform surfaces completed；
Step 7：Cladding vacuum bag is required according to solar cell substrate and vacuumized；
Step 8：Heated according to the solidifying requirements of solar cell substrate, cure under pressure；
Step 9：After the completion of solidification, cooling processing is carried out according to carbon fibre initial rinse fabric solidifying requirements；
Step 10：Required to remove vacuum plant according to the demoulding of solar cell substrate, it is suitable according to the installation of glass mold
Sequence removes mould, carries out demoulding processing；
Step 11：Solar cell substrate blank is cut according to the basic drawing requirement of solar cell；
Step 12：Brushwork epoxy resin glue is surveyed in the edge strip reinforcement completed, edge strip reinforcement is bonded；
Step 13：Heating cure is carried out according to epoxide-resin glue condition of cure.
The advantage of the invention is that：
(1) present invention makes for the solar cell substrate of stratosphere flight device and provides a kind of new method, this method
Technique is relatively easy, and preferably, product intensity is higher, lightweight, and producing efficiency is higher for final product quality.
(2) present invention uses sandwich sandwich technique, effectively raises the bearing capacity of solar cell substrate；
(3) present invention uses sandwich sandwich technique, uses honeycomb to significantly reduce solar cell substrate for enhancement layer
Weight
(4) present invention uses built-in connection local strengthening, and the strong of link position is ensure that in the case where outward appearance is consistent
Degree；
(5) present invention employs vacuum technique, the bubble existed when discharging and make by vacuum effectively raises finished product
Rate；
(6) present invention employs muscle girder construction, the flexural strength of solar cell substrate is effectively raised；
(7) present invention employs edge strip muscle girder construction, it is ensured that the peel strength of solar cell substrate；
(8) present invention employs hot-pressing technique, by integrally being pressurizeed to mould, it is ensured that solar cell substrate is solid
Pressure is consistent during change, it is to avoid deformation or alveolate situation caused by unbalance stress.
(9) the ultralight solar cell substrate of composite that the inventive method makes improves the energy of stratosphere flight device
Performance, it is ensured that reduce own wt while integral rigidity and stability, improves the operating efficiency of cell panel.
Brief description of the drawings
Fig. 1 is flow chart of the method for the present invention；
Fig. 2 is the solar cell substrate sandwich structure schematic diagram in the embodiment of the present invention；
Fig. 3 is the model schematic in the embodiment of the present invention；
Fig. 4 is the built-in connection schematic layout pattern in the embodiment of the present invention；
Fig. 5 is the shaping schematic view in the embodiment of the present invention；
Fig. 6 is built-in connection schematic diagram in the present invention；
In figure：1-1K carbon fiber twill weaves cloth, 2-aramid fiber paper honeycomb, 3-long side reinforcement
4-short side reinforcement, 5-fillet reinforcement, 6-built-in connection
7-glass mold, 8-cell substrates prefabricated component, 9-vacuum bag
10-vacuum nozzle.
Embodiment
The present invention is described in further detail below in conjunction with accompanying drawing：
The present invention is to carry out method according to the conventional structure standard of solar cell substrate structure to specify.
Correlation technique of the present invention has carbon fiber to be plated in technology, and honeycomb sandwich technique, sandwich structure is combined
Technology, vacuum coater technology, reinforcement girder construction technology, pre-buried interconnection technique, heating, cure under pressure method.
The present invention uses 1K carbon fiber twill weaves cloth 1 for raw material, uses poly (methyl methacrylate) plate for mould, carbon fibre initial rinse fabric
Edge strip reinforcement is made, built-in connection 6, the placing battery substrate prefabricated component in glass mold 7 are made using polycarbonate plate
8, when glass mold 7 is overall to be vacuumized, empty chamber air is discharged with vacuum nozzle 10, and as resin glued membrane softens, autoclave is led to
Cross glass mold 7 and pressure is provided, improve the quality of solar cell substrate, heated by resin glued membrane program curing design temperature
Solidification, cuts cell substrates prefabricated component after the completion of solidification, being bonded edge strip reinforcement by epoxide-resin glue improves cell substrates
Peel strength and flexural strength.
Reinforcement such as Fig. 3 of the ultralight solar cell substrate of composite, figure is included by two groups long side reinforcement 3, two
Group short side reinforcement 4 and four groups of fillet reinforcements 5 are connected with each other the rectangular shaped rim surrounded.
The ultralight solar cell substrate built-in connection 6 of composite of the present invention is as shown in fig. 6, in rectangular block shape structure
On symmetrically offer two through holes, built-in connection built-in connection layout is as shown in figure 4, by built-in connection 6 and aramid paper
Honeycomb 2 carries out bonding built-in connection using resin glued membrane.
In Fig. 1, the block diagram for the preparation method that the present invention is designed is shown, the present invention is on the ultralight solar-electricity of composite
The step of preparation method of pond substrate, is as follows：
Step one：According to the design requirement of the ultralight solar cell substrate of composite, edge strip reinforcement is made；
Edge strip reinforcement according to Fig. 3, designs the edge strip reinforcement of solar cell substrate, and edge strip reinforcement is used
3K carbon fibre initial rinse fabrics pass through molding；
Step 2：Required according to the laying of the ultralight solar cell substrate of composite, prepare 1K carbon fiber twill weaves
Cloth 1, aramid fiber paper honeycomb 2, epoxy resin glued membrane；
Step 3：Such as Fig. 4 is in the pre-buried fixed built-in connection 6 in the relevant position of aramid fiber paper honeycomb 2, and built-in connection 6 is poly-
Carbonic ester plate is obtained by machining；
Step 4：Epoxy resin glued membrane is plated in the upper and lower surface of aramid fiber paper honeycomb 2 of pre-buried completion, temperature control is plated in and exists
23 ± 3 degrees Celsius, it is plated in and uniformly avoids starved phenomenon, make its sandwich structure as shown in Figure 2；
Step 5：The 1K carbon fiber twill weaves cloth 1 of primary load bearing layer is plated according to solar cell substrate laying, was plated in
The braiding of journey carbon fiber, which need to be more than, is plated in glued membrane size 10cm or so；
Step 6：Glass mold 7 is fixed in the compound solar cell substrate preform surfaces completed, such as Fig. 5 is according to too
Positive energy cell substrates require cladding vacuum bag and vacuumized；
Step 7：Heated according to the solidifying requirements of solar cell substrate epoxy resin glued membrane, cure under pressure；
Autoclave heating, cure under pressure program are set, program curing is：Vacuum 1 standard atmospheric pressure entirety,
Solidified into autoclave, 1. room temperature is to 80 degrees Celsius of 0.5h, 0.5 standard atmospheric pressure of atmospheric pressure；2. 80 DEG C to 125 it is Celsius
2h is spent, atmospheric pressure rises to 1 standard atmospheric pressure；3. 125 DEG C insulation, pressurize 1.5h；
Step 8：After the completion of solidification, cooling processing is carried out according to carbon fibre initial rinse fabric solidifying requirements；
Step 9：Required to remove vacuum plant according to the demoulding of solar cell substrate, torn open according to the erection sequence of mould
Except glass mold, demoulding processing is carried out；The mould that solidification is completed is taken out from autoclave, room temperature is cooled to, vacuum bag is opened, take
Lower mold, takes out solar cell substrate product；
Step 10：Solar cell substrate blank is cut according to the basic drawing requirement of solar cell, cutting process will
Ensure that cell substrates size and otch are smooth；
Step 12：Brushwork epoxy resin glue is surveyed in the edge strip reinforcement completed, edge strip reinforcement is bonded；
Step 13：Heating cure is carried out according to epoxide-resin glue condition of cure；
Step 14：Normal temperature is naturally cooled to, solar cell substrate is taken out；
Finally, the ultralight solar cell substrate of composite is tested, complete make after finished product as shown in Figure 3.
Above-described embodiment is simply to illustrate that the technical concepts and features of the present invention, the purpose is to be to allow in the art
Those of ordinary skill can understand present disclosure and implement according to this, and it is not intended to limit the scope of the present invention.It is all
It is the equivalent change or modification according to made by the essence of present invention, should all covers within the scope of the present invention.
Claims (3)
1. the preparation method of the ultralight solar cell substrate of composite, it is characterised in that comprise the following steps：
(1) according to the design requirement of solar cell substrate, edge strip reinforcement is made；
(2) required according to the laying of solar cell substrate, prepare carbon fibre initial rinse fabric；
(3) according to solar cell substrate requirement in the pre-buried fixedly connected part in aramid fiber paper honeycomb relevant position；
(4) it is plated in epoxy resin glued membrane in the aramid fiber paper honeycomb upper and lower surface of pre-buried completion
(5) the 1K carbon fiber twill weave cloth of primary load bearing layer is plated according to solar cell substrate laying；
(6) glass mold is fixed in the compound solar cell substrate preform surfaces completed；
(7) cladding vacuum bag is required according to solar cell substrate and vacuumized；
(8) heated according to the solidifying requirements of solar cell substrate, cure under pressure；
(9) after the completion of solidifying, cooling processing is carried out according to carbon fibre initial rinse fabric solidifying requirements；
(10) required to remove vacuum plant according to the demoulding of solar cell substrate, mould is removed according to the erection sequence of glass mold
Tool, carries out demoulding processing；
(11) solar cell substrate blank is cut according to the basic drawing requirement of solar cell；
(12) brushwork epoxy resin glue is surveyed in the edge strip reinforcement completed, edge strip reinforcement is bonded；
(13) heating cure is carried out according to epoxide-resin glue condition of cure.
2. the preparation method of the ultralight solar base plate of composite according to claim 1, it is characterised in that：Described side
Bar reinforcement includes long side reinforcement, short side reinforcement and fillet reinforcement, and passes through long side, short side and fillet reinforcement
It is interconnected to form rectangular shaped rim.
3. the preparation method according to claim 1 for meeting the ultralight solar base plate of material, it is characterised in that：Described company
Fitting is that makrolon is obtained by machining.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710350246.5A CN107039561A (en) | 2017-05-18 | 2017-05-18 | The preparation method of the ultralight solar cell substrate of composite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710350246.5A CN107039561A (en) | 2017-05-18 | 2017-05-18 | The preparation method of the ultralight solar cell substrate of composite |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107039561A true CN107039561A (en) | 2017-08-11 |
Family
ID=59538665
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710350246.5A Pending CN107039561A (en) | 2017-05-18 | 2017-05-18 | The preparation method of the ultralight solar cell substrate of composite |
Country Status (1)
| Country | Link |
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| CN (1) | CN107039561A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108183181A (en) * | 2017-12-27 | 2018-06-19 | 天津中科先进技术研究院有限公司 | Manufacturing method of electric vehicle battery pack and battery pack |
| CN108649023A (en) * | 2018-03-28 | 2018-10-12 | 宁波市鄞州路麦电子有限公司 | A kind of lead frame and preparation method thereof |
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| CN102009501A (en) * | 2009-09-08 | 2011-04-13 | 上海卫星工程研究所 | Enhanced honeycomb sandwich structural slab and production method thereof |
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| CN108183181A (en) * | 2017-12-27 | 2018-06-19 | 天津中科先进技术研究院有限公司 | Manufacturing method of electric vehicle battery pack and battery pack |
| CN108649023A (en) * | 2018-03-28 | 2018-10-12 | 宁波市鄞州路麦电子有限公司 | A kind of lead frame and preparation method thereof |
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Application publication date: 20170811 |