CN106816479A - Flexible solar cell array suitable for near space ultra-long time-of-flight aircraft - Google Patents
Flexible solar cell array suitable for near space ultra-long time-of-flight aircraft Download PDFInfo
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- CN106816479A CN106816479A CN201611226357.7A CN201611226357A CN106816479A CN 106816479 A CN106816479 A CN 106816479A CN 201611226357 A CN201611226357 A CN 201611226357A CN 106816479 A CN106816479 A CN 106816479A
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- 229920006254 polymer film Polymers 0.000 claims abstract description 23
- 229920000098 polyolefin Polymers 0.000 claims abstract description 21
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical group [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims abstract description 13
- 229910001218 Gallium arsenide Inorganic materials 0.000 claims abstract description 11
- YCKRFDGAMUMZLT-UHFFFAOYSA-N Fluorine atom Chemical compound [F] YCKRFDGAMUMZLT-UHFFFAOYSA-N 0.000 claims abstract description 9
- 239000000853 adhesive Substances 0.000 claims abstract description 9
- 230000001070 adhesive effect Effects 0.000 claims abstract description 9
- 229910052731 fluorine Inorganic materials 0.000 claims abstract description 9
- 239000011737 fluorine Substances 0.000 claims abstract description 9
- 239000012943 hotmelt Substances 0.000 claims abstract description 8
- 238000003475 lamination Methods 0.000 claims abstract description 8
- 239000002313 adhesive film Substances 0.000 claims description 13
- JBRZTFJDHDCESZ-UHFFFAOYSA-N AsGa Chemical compound [As]#[Ga] JBRZTFJDHDCESZ-UHFFFAOYSA-N 0.000 claims description 9
- 229920002313 fluoropolymer Polymers 0.000 claims description 9
- 239000004811 fluoropolymer Substances 0.000 claims description 9
- 229910052802 copper Inorganic materials 0.000 claims description 5
- 239000010949 copper Substances 0.000 claims description 5
- 239000004831 Hot glue Substances 0.000 claims description 4
- 238000007493 shaping process Methods 0.000 claims description 4
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical group C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 3
- 150000001875 compounds Chemical class 0.000 claims 2
- 238000004806 packaging method and process Methods 0.000 abstract 1
- 238000010248 power generation Methods 0.000 abstract 1
- 239000010408 film Substances 0.000 description 21
- 238000003466 welding Methods 0.000 description 5
- 229920001577 copolymer Polymers 0.000 description 4
- 230000005611 electricity Effects 0.000 description 4
- 125000001153 fluoro group Chemical group F* 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 238000009304 pastoral farming Methods 0.000 description 4
- 239000011248 coating agent Substances 0.000 description 3
- 238000000576 coating method Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 239000003292 glue Substances 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 239000010409 thin film Substances 0.000 description 3
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 2
- BQCADISMDOOEFD-UHFFFAOYSA-N Silver Chemical compound [Ag] BQCADISMDOOEFD-UHFFFAOYSA-N 0.000 description 2
- 229910052782 aluminium Inorganic materials 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 2
- 238000005452 bending Methods 0.000 description 2
- 238000009954 braiding Methods 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 238000002474 experimental method Methods 0.000 description 2
- 239000011521 glass Substances 0.000 description 2
- 230000002787 reinforcement Effects 0.000 description 2
- 229910052710 silicon Inorganic materials 0.000 description 2
- 239000010703 silicon Substances 0.000 description 2
- 229910052709 silver Inorganic materials 0.000 description 2
- 239000004332 silver Substances 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- GYHNNYVSQQEPJS-UHFFFAOYSA-N Gallium Chemical compound [Ga] GYHNNYVSQQEPJS-UHFFFAOYSA-N 0.000 description 1
- ATJFFYVFTNAWJD-UHFFFAOYSA-N Tin Chemical compound [Sn] ATJFFYVFTNAWJD-UHFFFAOYSA-N 0.000 description 1
- 238000004026 adhesive bonding Methods 0.000 description 1
- 239000002390 adhesive tape Substances 0.000 description 1
- 229910052785 arsenic Inorganic materials 0.000 description 1
- RQNWIZPPADIBDY-UHFFFAOYSA-N arsenic atom Chemical compound [As] RQNWIZPPADIBDY-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 230000015271 coagulation Effects 0.000 description 1
- 238000005345 coagulation Methods 0.000 description 1
- 239000013078 crystal Substances 0.000 description 1
- 229910021419 crystalline silicon Inorganic materials 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 238000007667 floating Methods 0.000 description 1
- 238000005187 foaming Methods 0.000 description 1
- 238000013467 fragmentation Methods 0.000 description 1
- 238000006062 fragmentation reaction Methods 0.000 description 1
- 229910052733 gallium Inorganic materials 0.000 description 1
- 239000012774 insulation material Substances 0.000 description 1
- 238000010030 laminating Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000012528 membrane Substances 0.000 description 1
- 229910021421 monocrystalline silicon Inorganic materials 0.000 description 1
- 239000000178 monomer Substances 0.000 description 1
- 239000005022 packaging material Substances 0.000 description 1
- 229910021420 polycrystalline silicon Inorganic materials 0.000 description 1
- 230000008092 positive effect Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000003860 storage Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000005496 tempering 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
- H01L31/02—Details
- H01L31/02002—Arrangements for conducting electric current to or from the device in operations
- H01L31/02005—Arrangements for conducting electric current to or from the device in operations for device characterised by at least one potential jump barrier or surface barrier
- H01L31/02008—Arrangements for conducting electric current to or from the device in operations for device characterised by at least one potential jump barrier or surface barrier for solar cells or solar cell modules
- H01L31/0201—Arrangements for conducting electric current to or from the device in operations for device characterised by at least one potential jump barrier or surface barrier for solar cells or solar cell modules comprising specially adapted module bus-bar structures
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01L—SEMICONDUCTOR DEVICES NOT COVERED BY CLASS H10
- H01L31/00—Semiconductor devices sensitive to infrared radiation, light, electromagnetic radiation of shorter wavelength or corpuscular radiation and specially adapted either for the conversion of the energy of such radiation into electrical energy or for the control of electrical energy by such radiation; Processes or apparatus specially adapted for the manufacture or treatment thereof or of parts thereof; Details thereof
- H01L31/02—Details
- H01L31/0224—Electrodes
- H01L31/022408—Electrodes for devices characterised by at least one potential jump barrier or surface barrier
- H01L31/022425—Electrodes for devices characterised by at least one potential jump barrier or surface barrier for solar cells
-
- 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
- H01L31/0248—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 characterised by their semiconductor bodies
- H01L31/0256—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 characterised by their semiconductor bodies characterised by the material
- H01L31/0264—Inorganic materials
- H01L31/0304—Inorganic materials including, apart from doping materials or other impurities, only AIIIBV compounds
-
- 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
- H01L31/0445—PV modules or arrays of single PV cells including thin film solar cells, e.g. single thin film a-Si, CIS or CdTe solar cells
-
- 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
- Y02E10/544—Solar cells from Group III-V materials
Abstract
The invention relates to a flexible solar cell array suitable for an ultra-long time flight aircraft in a near space. The invention belongs to the technical field of physical power supplies. The flexible solar cell array is suitable for an ultra-long aircraft in a near space, a transparent fluorine-containing polymer film, a polyolefin film, a cell string, a polyolefin film and a sequential lamination of a transparent or white polymer film are sequentially arranged from top to bottom, the cell string adopts a flexible multijunction gallium arsenide cell as a power generation unit, a cell overlapping contact mode is adopted, series-parallel connection between cells is realized, a bus bar adopts a silver-plated copper core to weave a flat flexible wire, the upper surface of a component adopts the fluorine-containing polymer film, the lower surface of the component adopts the transparent or white polymer film for packaging, an adhesive adopts a hot-melt polyolefin film, the front side and the back side of the cell string are respectively subjected to hot-melt adhesion with the fluorine-containing transparent polymer film and/or the white polymer film, and the. The invention has the advantages of firmness, reliability, flexible torsion, small mass surface density and high energy utilization rate.
Description
Technical field
It is more particularly to a kind of to be applied to aircraft when near space overlength is navigated the invention belongs to physical power source technical field
Flexible solar cell array.
Background technology
At present, aircraft is main using solar energy as main energy sources when near space overlength is navigated.Main Types include
Solar energy unmanned plane, electric power solar energy dirigible and aerostatics etc..This kind of aircraft is because flying height is high, flying speed is slow,
Flight time is long, therefore solar battery array to undertaking generating function proposes technical requirements very high.One will have higher
Conversion efficiency.Being applied to the solar battery array of aircraft when near space overlength is navigated at present mainly has two kinds, and one kind is based on crystalline substance
The semi-flexible solar battery array of silicon rigidity battery, one kind is based on flexible thin-film battery (such as CIGS, non-crystalline silicon, film arsenic
Change gallium etc.) Grazing condition solar battery array.Semi-flexible efficiency of solar array is moderate, and cost is relatively low, at home and abroad solar energy without
Man-machine upper extensive use, but because its surface density is high, there is no method to realize staying sky for a long time at present；And Grazing condition solar battery array is curved
Qu Nengli is strong, and surface density is low, is applied more broadly on aerostatics and unmanned plane.Wherein turned with thin film gallium arsenide solar battery array
Change efficiency highest (30%), the minimum (350g/m of surface density2), it is most potential solar cell product of new generation, the current world
Each state is all promptly developing Related product.
Conventional photovoltaic component uses monocrystalline silicon or polycrystalline silicon solar cell, with EVA PUR, tempering
Glass and TPT backsheet layer pressures are fabricated by.Although the solar module that this technique is produced can possess long-acting generating energy
Power, but its weight is big, inflexibility, limits its use near space vehicle.Even if after employ transparent PET
Instead of glass, still it is difficult to meet surface density requirement.
Semi-flexible solar battery array described in CN201410655911.8 is that one kind only can realize local buckling in folding position
Component, using thin crystal silicon rigidity battery as generator unit, it is impossible to after avoiding solar cell from being subject to internal bending or twisting resistance
The fragmentation for causing, it is therefore necessary to which the aluminum honeycomb panel that 3mm is not less than with thickness in the part containing battery carries out partial structurtes reinforcement,
Although simple aluminum honeycomb panel has been largely used to space industry, its density of texture is added at least in more than 600g/m2
After the weight of battery and glue, there is solar battery array weight will not be less than 900g/m2, full battle array conversion efficiency is not higher than 19% etc.
Problem.
The content of the invention
When the present invention provides a kind of boat suitable near space overlength to solve technical problem present in known technology
The flexible solar cell array of aircraft.
Large area is laid, firmly may be used on aircraft when it is an object of the invention to provide one kind there is near space overlength to navigate
By the small Grazing condition thin film solar battery array row of, flexible torsion, mass surface density, the efficient stable of solar cell power is realized
The flexible solar cell array of aircraft when being navigated suitable near space overlength of the features such as output.
Innovation point of the invention includes：
Using Grazing condition film multi-junction gallium arsenide battery, and innovation design is carried out in battery device technique.Flexibility is too
Positive cell backside is designed as the copper coating of conduction, and front main grid is optimized design, reduces primary gate electrode highly, increases main grid
Width, be beneficial to and be fully contacted with the copper back electrode of another battery by containing silver conductive adhesive.
Using series connection direction successively stacked tile type battery circuit attachment structure, the use of welding and interconnection piece is greatly reduced,
Improve the reliability and flatness of group battle array.This kind of type of attachment can also effectively improve effective pieces of cloth rate of group battle array, Jin Erti
The generated output of unit area high.
Array foreboard and backboard innovation use fluoro-containing copolymer film, 12.5~25 microns of film thickness to play protection
The effect of battery circuit, and certain mechanical load can be carried.The constraint of liner plate or backboard reinforcement material is thoroughly broken away from, is really reached
Structure is arrived integrated with circuit.
Array both positive and negative polarity lead-out wire is drawn by with the flat flexible cord of braiding that busbar is welded perpendicular to group array edge, flat flexible cord
Be a kind of special flat silver-plated copper wire harness with minor insulation material, it is advantageous that can through by bending, stretching, reverse
And keep the stable output state of cable.
The flexible solar cell array of aircraft is adopted the technical scheme that when the present invention navigates suitable near space overlength：
A kind of flexible solar cell array of aircraft when being navigated suitable near space overlength, is characterized in：Flexible sun electricity
Chi Zhen is successively from top to bottom clear fluoropolymer film, polyolefin adhesive film, battery strings, polyolefin adhesive film, transparent or white
The order lamination of polymer film, battery strings use flexible multi-junction gallium arsenide battery as generator unit, using battery overlapping contact
Mode, realizes the connection in series-parallel between battery, and busbar weaves flat flexible cord using silver-plated copper core, and component upper surface is using transparent fluorine-containing
Thin polymer film is made, and lower surface is packaged using transparent or white polymer film, and adhesive is using hot melt polyolefin glue
Film, hot melt adhesive is carried out in battery strings tow sides with fluorine-containing transparent polymer film and/or white polymer film respectively, soft
Property high temperature of solar battery array is laminated into type.
The flexible solar cell array of aircraft can also use following technology when the present invention navigates suitable near space overlength
Scheme：
The described flexible solar cell array of aircraft when being navigated suitable near space overlength, is characterized in：The flexible sun
Outer rim takes making copper colligation hole, the back side to paste magnetic sticky buckle and directly and carbon fiber structural after the shaping of cell array array
The mode that part is glued is realized mechanically connecting with body.
The described flexible solar cell array of aircraft when being navigated suitable near space overlength, is characterized in：Battery strings are adopted
With the flexible multi-junction gallium arsenide battery that thickness is 20-50 microns as generator unit.
The described flexible solar cell array of aircraft when being navigated suitable near space overlength, is characterized in：Component upper table
Face is made of 10-15 microns of thick clear fluoropolymer film, and lower surface is using 20-30 microns of thick transparent or white
Thin polymer film is packaged.
The described flexible solar cell array of aircraft when being navigated suitable near space overlength, is characterized in：Adhesive is adopted
With 20-50 microns of polyolefin hot-melt film.
The present invention has the advantages and positive effects that：
The flexible solar cell array of aircraft is as a result of the brand-new skill of the present invention when being navigated suitable near space overlength
Art scheme, compared with prior art, the present invention includes following characteristics：
1st, the material encapsulated as positive and negative using fluoro-containing copolymer film, surface is blocked water coating, effectively prevents water
Influence of the vapour to battery life；
2nd, battery is flexibility, and replaces welding using stacked tile type series system, effectively improves group battle array flatness and a stability,
And array can free bend, when radius of curvature reaches 50mm, performance is without influence；
3rd, this patent uses efficient flexible multi-junction gallium arsenide battery, and efficiency, can be according to the actual requirements more than 31%
Size carries out Array Design combination.Component best power point power-weight ratio is more than 600W/kg；
4th, component is made of Ultrathin packaging material and slimline battery, and after combination, component thickness is only 180 microns, component
Surface density 350g/m2；
5th, the resistance to environment capacity of component is strong, and power declines drop less than 2% after ultraviolet irradiation experiment in 10 days.Component experience 10 days it is damp and hot
After experiment, power declines drop less than 3%, -80 DEG C~80 DEG C temperature alternatings of scope is can tolerate, 30 days under low pressure 4kPa environment
Storage, the phenomenons such as foaming of not coming unglued；
6 interfaces integrated with Flight Vehicle Structure are friendly, not cracky.
Aircraft when high-altitude overlength is navigated is made using the solar battery array of this efficient, high-specific-power, areal density to generate electricity
Module, can effectively reduce energy resource system weight, improve efficiency of energy utilization.By integrated design, solar battery array can be with
As solar energy unmanned plane skin material.
Brief description of the drawings
Fig. 1 applies to the flexible solar cell array internal structure schematic diagram of aircraft when near space overlength is navigated；
Fig. 2 applies to the flexible solar cell array structural representation of aircraft when near space overlength is navigated.
In figure, 1- clear fluoropolymer films, 2- polyolefin adhesive films, 3- solar cells, 4- back polymer films, 5-
Silver-plated copper core weaves flat flexible cord, 6- conductive tapes.
Specific embodiment
For the content of the invention of the invention, feature and effect can be further appreciated that, following examples are hereby enumerated, and coordinate accompanying drawing
Describe in detail as follows：
Refering to accompanying drawing 1 and Fig. 2.
Embodiment 1
A kind of flexible solar cell array of aircraft when being navigated suitable near space overlength, is successively from top to bottom transparent containing
Fluoropolymer film, polyolefin adhesive film, battery strings, polyolefin adhesive film, transparent or white polymeric films order lamination, battery strings
Using flexible multi-junction gallium arsenide battery as generator unit, using battery overlapping contact mode, the connection in series-parallel between battery is realized,
Busbar weaves flat flexible cord using silver-plated copper core, and component upper surface is made of clear fluoropolymer film, and lower surface is used
Transparent or white polymer film is packaged, adhesive using hot melt polyolefin adhesive film, battery strings tow sides respectively with
Fluorine-containing transparent polymer film and/or white polymer film carry out hot melt adhesive, high temperature lamination of flexible solar cell array
Shaping.
The flexible solar cell array of aircraft when being navigated suitable near space overlength：
Used as generator unit, monomer efficiency exceedes the flexible multi-junction gallium arsenide battery for being not more than 50 microns using thickness
31%, combined efficiency is up to 30% (1280W/m2, 2km, 25 DEG C).
By way of battery overlapping contact, the connection in series-parallel between battery is realized, save the welding process of battery series-parallel connection.
Busbar weaves flat flexible cord using silver-plated copper core, it is ensured that array will not cause busbar normal direction warpage under the conditions of hot alternation.
Component upper surface is made of the clear fluoropolymer film of 12.5 microns of thickness, and lower surface is transparent using 25 microns
Or white polymer film is packaged.
Adhesive use less than 50 microns polyolefin hot-melt films, battery strings tow sides respectively with fluorine-containing transparent polymeric
Thing film and white polymer film carry out hot melt adhesive.
Solar battery array is successively from top to bottom clear fluoropolymer film, polyolefin adhesive film, battery strings, polyolefin glue
Film, transparent or white polymeric films order lamination, it is laminated into type by a high temperature.
According to different technical requirements, outer rim can take making copper colligation hole, the back side to paste magic after array shaping
Thread gluing and the mode being directly glued with carbon fiber structural part are realized mechanically connecting with body.Fully meet dirigible, floating gas
The kinds of platform design requirement such as ball, unmanned plane.
The specific manufacturing process of the present embodiment：
Series connection makes：Refering to accompanying drawing 1, the flexible gallium arsenide cells 3 from 2mm × 4mm are some, first in every battery front side
By automatic dispensing machine, uniformly one layer of coating contains silver conductive adhesive on main grid, then by each battery by manually or automatically equipment
Mode is placed on series welding mould successively, and the main grid of adjacent cell and backplate are bonded together, and forms a battery strings,
4 identical battery strings have been made in example, after conducting resinl natural coagulation is cemented, then a group battle array mould has been fully transferred to
On, group battle array mould is used to control the gap of each string battery, is connected to the head and the tail of 4 string batteries eventually through conductive tape 6
Together, array is formed.The half of conductive tape 6 is overlapped on battery, and half is exposed at outside cell array, and electricity is drawn for welding electrode
Cable.
The making of electrode：One of the silver-plated copper core flat flexible cord 5 of braiding is welded therewith with a small amount of scolding tin on conductive tape
Fixed, wire direction is vertical with conductive tape holding, and the other end retains a part of insulated hull as electrode leads to client.Every is led
2 wires are at least welded on electric adhesive tape as electrode.
Lamination makes：The good battery circuit face down of combinations thereof is placed on the fluoro-containing copolymer film 1 completed in advance
On polyolefin adhesive film 2, laminated layer sequence is followed successively by fluoro-containing copolymer film 1, polyolefin adhesive film 2, battery circuit 3 from bottom to top.
Second layer polyolefin adhesive film 2, back polymer film 4 are covered on above-mentioned laminated construction successively again.Finally by reserved electricity
Pole exit is passed from notacoria.
Laminates：Be placed on above-mentioned laminated construction on laminating machine by the mode from multistage vacuum lamination, is laminated 1 hour
After take out, after cutting unnecessary glued membrane, you can obtain the embodiment shown in accompanying drawing 1.
The present embodiment has solid and reliable, flexible torsion, mass surface density small, can effectively reduce energy resource system weight
Amount, improves efficiency of energy utilization, can carry out large area laying with integrated design, realizes the efficient stable of solar cell power
The good effects such as output.
Claims (5)
1. a kind of flexible solar cell array of aircraft when being navigated suitable near space overlength, it is characterized in that：Flexible solar cell
Battle array is successively from top to bottom clear fluoropolymer film, polyolefin adhesive film, battery strings, polyolefin adhesive film, transparent or white poly-
The order lamination of compound film, battery strings use flexible multi-junction gallium arsenide battery as generator unit, using battery overlapping contact side
Formula, realizes the connection in series-parallel between battery, and busbar weaves flat flexible cord using silver-plated copper core, and component upper surface is using transparent fluorine-containing poly-
Compound film is made, and lower surface is packaged using transparent or white polymer film, and adhesive uses hot melt polyolefin adhesive film,
Hot melt adhesive is carried out with fluorine-containing transparent polymer film and/or white polymer film respectively in battery strings tow sides, it is flexible
High temperature of solar battery array is laminated into type.
2. the flexible solar cell array of aircraft when being navigated suitable near space overlength according to claim 1, its feature
It is：Outer rim takes making copper colligation hole, the back side to paste magnetic sticky buckle and directly after the shaping of flexible solar cell array array
The mode being glued with carbon fiber structural part is realized mechanically connecting with body.
3. the flexible solar cell array of aircraft when being navigated suitable near space overlength according to claim 1 and 2, it is special
Levying is：It is 20-50 microns of flexible multi-junction gallium arsenide battery as generator unit that battery strings use thickness.
4. the flexible solar cell array of aircraft when being navigated suitable near space overlength according to claim 1 and 2, it is special
Levying is：Component upper surface is made of 10-15 microns of thick clear fluoropolymer film, and lower surface uses 20-30 microns
Thick transparent or white polymer film is packaged.
5. the flexible solar cell array of aircraft when being navigated suitable near space overlength according to claim 1 and 2, it is special
Levying is：Adhesive uses 20-50 microns of polyolefin hot-melt film.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611226357.7A CN106816479A (en) | 2016-12-27 | 2016-12-27 | Flexible solar cell array suitable for near space ultra-long time-of-flight aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611226357.7A CN106816479A (en) | 2016-12-27 | 2016-12-27 | Flexible solar cell array suitable for near space ultra-long time-of-flight aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106816479A true CN106816479A (en) | 2017-06-09 |
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|---|---|---|---|
| CN201611226357.7A Pending CN106816479A (en) | 2016-12-27 | 2016-12-27 | Flexible solar cell array suitable for near space ultra-long time-of-flight aircraft |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109103284A (en) * | 2018-08-02 | 2018-12-28 | 东汉太阳能无人机技术有限公司 | Aircraft, solar cell system, wing and its manufacturing method |
| CN109860318A (en) * | 2017-11-29 | 2019-06-07 | 米亚索莱高科公司 | Busbar for flexible photovoltaic module |
| CN110600564A (en) * | 2019-09-17 | 2019-12-20 | 湖南纵横空天能源科技有限公司 | Flexible gallium arsenide component and manufacturing process |
| CN111193472A (en) * | 2018-11-15 | 2020-05-22 | 上海太阳能工程技术研究中心有限公司 | Flexible solar cell array for near space airship |
| CN112216753A (en) * | 2020-09-17 | 2021-01-12 | 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 |
| CN112909110A (en) * | 2021-01-14 | 2021-06-04 | 航天科工空间工程发展有限公司 | Flexible solar cell array adaptive to roll type solar wing |
| CN113364409A (en) * | 2021-06-30 | 2021-09-07 | 中国建材国际工程集团有限公司 | Foldable cadmium telluride thin film solar cell module and preparation method thereof |
| CN114162335A (en) * | 2020-09-11 | 2022-03-11 | 海鹰航空通用装备有限责任公司 | Near space vehicle energy storage battery thermal management system |
| CN115832089A (en) * | 2022-12-29 | 2023-03-21 | 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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| CN109860318A (en) * | 2017-11-29 | 2019-06-07 | 米亚索莱高科公司 | Busbar for flexible photovoltaic module |
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| CN114162335A (en) * | 2020-09-11 | 2022-03-11 | 海鹰航空通用装备有限责任公司 | Near space vehicle energy storage battery thermal management system |
| 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 |
| CN112216753A (en) * | 2020-09-17 | 2021-01-12 | 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 |
| CN112909110A (en) * | 2021-01-14 | 2021-06-04 | 航天科工空间工程发展有限公司 | Flexible solar cell array adaptive to roll type solar wing |
| CN113364409A (en) * | 2021-06-30 | 2021-09-07 | 中国建材国际工程集团有限公司 | Foldable cadmium telluride thin film solar cell module and preparation method thereof |
| CN115832089A (en) * | 2022-12-29 | 2023-03-21 | 苏州馥昶空间技术有限公司 | Space flexible solar cell array and packaging method and application thereof |
| 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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