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 PDF

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Publication number
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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CN
China
Prior art keywords
solar cell
cell substrate
reinforcement
ultralight
edge strip
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Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN201710350246.5A
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Chinese (zh)
Inventor
宋庆春
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Qingdao Three Hop Xinghua Science And Technology Development Co Ltd
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Qingdao Three Hop Xinghua Science And Technology Development Co Ltd
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Priority to CN201710350246.5A priority Critical patent/CN107039561A/en
Publication of CN107039561A publication Critical patent/CN107039561A/en
Pending legal-status Critical Current

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    • HELECTRICITY
    • H01BASIC ELECTRIC ELEMENTS
    • H01LSEMICONDUCTOR DEVICES; ELECTRIC SOLID STATE DEVICES NOT OTHERWISE PROVIDED FOR
    • H01L31/00Semiconductor devices sensitive to infra-red 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
    • H01L31/04Semiconductor devices sensitive to infra-red 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
    • H01L31/042PV modules or arrays of single PV cells
    • H01L31/048Encapsulation of modules
    • H01L31/0481Encapsulation of modules characterised by the composition of the encapsulation material
    • HELECTRICITY
    • H01BASIC ELECTRIC ELEMENTS
    • H01LSEMICONDUCTOR DEVICES; ELECTRIC SOLID STATE DEVICES NOT OTHERWISE PROVIDED FOR
    • H01L31/00Semiconductor devices sensitive to infra-red 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
    • H01L31/18Processes or apparatus specially adapted for the manufacture or treatment of these devices or of parts thereof
    • YGENERAL 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
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02EREDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00Energy generation through renewable energy sources
    • Y02E10/50Photovoltaic [PV] energy

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

The preparation method of the ultralight solar cell substrate of composite
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.
CN201710350246.5A 2017-05-18 2017-05-18 The preparation method of the ultralight solar cell substrate of composite Pending CN107039561A (en)

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Application Number Priority Date Filing Date Title
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Cited By (2)

* Cited by examiner, † Cited by third party
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 A kind of production method and battery pack of batteries of electric automobile packet
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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CN106364025A (en) * 2016-08-29 2017-02-01 铱格斯曼航空科技集团有限公司 Composite sandwich plate and producing method thereof
CN106393902A (en) * 2016-08-30 2017-02-15 铱格斯曼航空科技集团有限公司 Nanometer modified capsule material for high-altitude aerostat and preparation method thereof
CN106427110A (en) * 2016-08-30 2017-02-22 铱格斯曼航空科技集团有限公司 Outer skin material for hangar, and preparation method of outer skin material
CN106626543A (en) * 2015-11-04 2017-05-10 宜兴市中碳科技有限公司 Directly-plastic-bound epoxy-based carbon fiber plate

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CN101320760A (en) * 2008-07-11 2008-12-10 北京航空航天大学 Solar cell module and preparation method thereof
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
CN103846981A (en) * 2012-11-29 2014-06-11 大连飞马文仪家俱有限公司 Light composite board
CN205202333U (en) * 2015-11-04 2016-05-04 宜兴市中碳科技有限公司 Direct plastic combines epoxy base carbon fiber board
CN106626543A (en) * 2015-11-04 2017-05-10 宜兴市中碳科技有限公司 Directly-plastic-bound epoxy-based carbon fiber plate
CN205086002U (en) * 2015-11-16 2016-03-16 哈尔滨泓鑫数控机电工程有限公司 Honeycomb carbon -fibre composite connecting piece
CN105936132A (en) * 2016-05-11 2016-09-14 铱格斯曼航空科技集团有限公司 Preparation method for mold of carbon fiber composite integrated shell structure
CN106364025A (en) * 2016-08-29 2017-02-01 铱格斯曼航空科技集团有限公司 Composite sandwich plate and producing method thereof
CN106393902A (en) * 2016-08-30 2017-02-15 铱格斯曼航空科技集团有限公司 Nanometer modified capsule material for high-altitude aerostat and preparation method thereof
CN106427110A (en) * 2016-08-30 2017-02-22 铱格斯曼航空科技集团有限公司 Outer skin material for hangar, and preparation method of outer skin material
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Cited By (3)

* Cited by examiner, † Cited by third party
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 A kind of production method and battery pack of batteries of electric automobile packet
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
CN108649023B (en) * 2018-03-28 2020-03-03 宁波市鄞州路麦电子有限公司 Lead frame and preparation method thereof

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Application publication date: 20170811