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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- H—ELECTRICITY
- H10—SEMICONDUCTOR DEVICES; ELECTRIC SOLID-STATE DEVICES NOT OTHERWISE PROVIDED FOR
- H10F—INORGANIC SEMICONDUCTOR DEVICES SENSITIVE TO INFRARED RADIATION, LIGHT, ELECTROMAGNETIC RADIATION OF SHORTER WAVELENGTH OR CORPUSCULAR RADIATION
- H10F77/00—Constructional details of devices covered by this subclass
- H10F77/93—Interconnections
- H10F77/933—Interconnections for devices having potential barriers
- H10F77/935—Interconnections for devices having potential barriers for photovoltaic devices or modules
- H10F77/937—Busbar structures for modules
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- H—ELECTRICITY
- H10—SEMICONDUCTOR DEVICES; ELECTRIC SOLID-STATE DEVICES NOT OTHERWISE PROVIDED FOR
- H10F—INORGANIC SEMICONDUCTOR DEVICES SENSITIVE TO INFRARED RADIATION, LIGHT, ELECTROMAGNETIC RADIATION OF SHORTER WAVELENGTH OR CORPUSCULAR RADIATION
- H10F19/00—Integrated devices, or assemblies of multiple devices, comprising at least one photovoltaic cell covered by group H10F10/00, e.g. photovoltaic modules
- H10F19/30—Integrated devices, or assemblies of multiple devices, comprising at least one photovoltaic cell covered by group H10F10/00, e.g. photovoltaic modules comprising thin-film photovoltaic cells
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- H—ELECTRICITY
- H10—SEMICONDUCTOR DEVICES; ELECTRIC SOLID-STATE DEVICES NOT OTHERWISE PROVIDED FOR
- H10F—INORGANIC SEMICONDUCTOR DEVICES SENSITIVE TO INFRARED RADIATION, LIGHT, ELECTROMAGNETIC RADIATION OF SHORTER WAVELENGTH OR CORPUSCULAR RADIATION
- H10F19/00—Integrated devices, or assemblies of multiple devices, comprising at least one photovoltaic cell covered by group H10F10/00, e.g. photovoltaic modules
- H10F19/80—Encapsulations or containers for integrated devices, or assemblies of multiple devices, having photovoltaic cells
- H10F19/804—Materials of encapsulations
-
- H—ELECTRICITY
- H10—SEMICONDUCTOR DEVICES; ELECTRIC SOLID-STATE DEVICES NOT OTHERWISE PROVIDED FOR
- H10F—INORGANIC SEMICONDUCTOR DEVICES SENSITIVE TO INFRARED RADIATION, LIGHT, ELECTROMAGNETIC RADIATION OF SHORTER WAVELENGTH OR CORPUSCULAR RADIATION
- H10F77/00—Constructional details of devices covered by this subclass
- H10F77/10—Semiconductor bodies
- H10F77/12—Active materials
- H10F77/124—Active materials comprising only Group III-V materials, e.g. GaAs
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- H—ELECTRICITY
- H10—SEMICONDUCTOR DEVICES; ELECTRIC SOLID-STATE DEVICES NOT OTHERWISE PROVIDED FOR
- H10F—INORGANIC SEMICONDUCTOR DEVICES SENSITIVE TO INFRARED RADIATION, LIGHT, ELECTROMAGNETIC RADIATION OF SHORTER WAVELENGTH OR CORPUSCULAR RADIATION
- H10F77/00—Constructional details of devices covered by this subclass
- H10F77/20—Electrodes
- H10F77/206—Electrodes for devices having potential barriers
- H10F77/211—Electrodes for devices having potential barriers for photovoltaic cells
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/50—Photovoltaic [PV] energy
- Y02E10/544—Solar cells from Group III-V materials
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Abstract
本发明涉及一种适用于临近空间超长航时飞行器的柔性太阳电池阵。本发明属于物理电源技术领域。适用于临近空间超长航时飞行器的柔性太阳电池阵，从上到下依次是透明含氟聚合物薄膜、聚烯烃胶膜、电池串、聚烯烃胶膜、透明或白色聚合物膜的顺序叠层，电池串采用柔性多结砷化镓电池作为发电单元，采用电池交叠接触方式，实现电池之间的串并联，汇流条采用镀银铜芯编织扁软线，组件上表面采用含氟聚合物薄膜，下表面采用透明或白色聚合物薄膜封装，粘合剂采用热熔聚烯烃胶膜，在电池串正反两面分别与含氟透明聚合物薄膜和/或白色聚合物薄膜进行热熔粘合，柔性太阳电池阵一次高温层压成型。本发明牢固可靠、可弯曲扭转、质量面密度小，能源利用率高。
The invention relates to a flexible solar array suitable for ultra-long-endurance aircraft in near space. The invention belongs to the technical field of physical power supply. A flexible solar array suitable for near space ultra-long-endurance aircraft, from top to bottom, is a sequential stack of transparent fluoropolymer film, polyolefin film, battery string, polyolefin film, and transparent or white polymer film. layer, the battery string uses flexible multi-junction gallium arsenide cells as the power generation unit. The battery overlapping contact method is used to realize series and parallel connection between batteries. The bus bar uses silver-plated copper core braided flat flexible wire, and the upper surface of the component is made of fluorine-containing polymer. The lower surface is encapsulated with a transparent or white polymer film, and the adhesive is a hot-melt polyolefin film. The front and back sides of the battery string are hot-melt-bonded with the fluorine-containing transparent polymer film and/or the white polymer film. Together, the flexible solar array is formed by high-temperature lamination in one step. The invention is strong and reliable, can be bent and twisted, has low mass area 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.
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| CN201611226357.7A 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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| CN201611226357.7A 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 | Bus bars for flexible photovoltaic modules |
| 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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| CN114162335B (en) * | 2020-09-11 | 2024-05-07 | 海鹰航空通用装备有限责任公司 | Energy storage battery thermal management system of near space vehicle |
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| 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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Application publication date: 20170609 |