CN203659894U - Lightweighting flexible solar cell assembly for solar airplane - Google Patents
Lightweighting flexible solar cell assembly for solar airplane Download PDFInfo
- Publication number
- CN203659894U CN203659894U CN201320848268.1U CN201320848268U CN203659894U CN 203659894 U CN203659894 U CN 203659894U CN 201320848268 U CN201320848268 U CN 201320848268U CN 203659894 U CN203659894 U CN 203659894U
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- thickness
- cell assembly
- solar cell
- solar
- etfe
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- 229920000840 ethylene tetrafluoroethylene copolymer Polymers 0.000 claims abstract description 27
- 229910021421 monocrystalline silicon Inorganic materials 0.000 claims abstract description 19
- 238000005538 encapsulation Methods 0.000 claims abstract description 5
- 238000004049 embossing Methods 0.000 claims description 6
- 239000010410 layer Substances 0.000 description 17
- 229920002725 thermoplastic elastomer Polymers 0.000 description 16
- 239000005038 ethylene vinyl acetate Substances 0.000 description 15
- 229920001200 poly(ethylene-vinyl acetate) Polymers 0.000 description 15
- 238000003475 lamination Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 238000005457 optimization Methods 0.000 description 3
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 2
- 238000005452 bending Methods 0.000 description 2
- 239000013078 crystal Substances 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 229910052710 silicon Inorganic materials 0.000 description 2
- 239000010703 silicon Substances 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000004146 energy storage Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000010006 flight Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 239000011229 interlayer Substances 0.000 description 1
- 238000010030 laminating Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 229910021420 polycrystalline silicon Inorganic materials 0.000 description 1
- 229920005591 polysilicon Polymers 0.000 description 1
- 229910000679 solder Inorganic materials 0.000 description 1
- 239000005437 stratosphere Substances 0.000 description 1
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Classifications
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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
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- Photovoltaic Devices (AREA)
Abstract
The utility model discloses a lightweighting flexible solar cell assembly for a solar airplane. The lightweighting flexible solar cell assembly comprises an ETFE light-transmission film, an EVA layer, a monocrystalline silicon piece and a TPE backboard which are successively encapsulated from top to bottom; and the thickness of the ETFE light-transmission film is 40 [mu]m to 60 [mu]m, the thickness of the EVA layer is 220 [mu]m to 300 [mu]m, the thickness of the monocrystalline silicon piece is 100 [mu]m to 160 [mu]m, and the thickness of the TPE backboard is 300 [mu]m o 360 [mu]m. The areal density of the solar cell assembly is reduced by at least about 35% compared with the areal density of a traditional solar cell assembly, its own weight of the solar cell assembly per unit area is greatly reduced, and thus the solar airplane can carry more task loads; and, furthermore, the encapsulation scheme also can enable the whole solar cell assembly to be more flexible, a restoring force and an internal stress of the solar cell assembly are small after moderate folding, and thus attachment performance of the solar cell assembly on machine body and wing surfaces is improved.
Description
Technical field
The utility model relates to solar module field, particularly relates to a kind of lightweight flexible solar cell assembly for solar powered aircraft.
Background technology
Driven by Solar Energy aircraft with respect to conventional fuel aircraft have pollution-free, the energy is sufficient, and flying height is high, can be in advantages such as stratosphere meters altitude flights.Because it is subject to atmospheric interference also less in the aerial flight stability of height, the flight time is long, if power, energy storage, solar cell collocation are rationally, its flight time is affected by the airplane parts life-span only, and theory can be for the several years.
In order to ensure that solar powered aircraft has enough flying powers, often need on its wing, fuselage, lay more solar module.But general 200 μ mPET light-transmissive film+500 μ mEVA layer+monocrystalline silicon pieces or the polysilicon chip+TPE backlight of adopting of traditional solar module, its surface density is generally 2.0 ~ 2.5 kg/m
2, because its structural design is unreasonable, cause the quality of solar module itself larger, and then increase the own wt of solar powered aircraft; And the overall design weight of solar powered aircraft is certain, if make the solar powered aircraft can aerial flight, this just must subdue the entrained detecting devices of solar powered aircraft or other equipment, and then has had a strong impact on the application performance of aircraft, has limited the scope of application of solar powered aircraft.
In addition, the light-transmissive film of the solar module on existing solar powered aircraft adopts PET material, the general design of EVA layer is thicker, and then cause the rigidity after solar module moulding larger, it has very large back stretch after adhering to aircraft surfaces, after installing, internal stress is very large, unreliable with body junction, is difficult for direct large area monoblock and installs; If adopt the assembled scheme of fritter, can make aircraft surfaces rough, there are a lot of crest lines, for originally obviously increasing with regard to the solar powered aircraft resistance of low speed, it is a lot of that lift-drag ratio is subject to crest line to affect decline, and aeroperformance will be had a strong impact on, and assembly is many because piece number welds point pole too much, when electric leakage has a big risk, increase solder joint weight.
Utility model content
For this reason, the technical problems to be solved in the utility model is that the existing solar module rigidity that is installed on solar powered aircraft is larger, causes that solar module back stretch after attaching on fuselage, wing is higher, internal stress is large, can not bulk install; And because the autologous density of solar module is larger, cause the equipments such as detection that solar powered aircraft can carry less, affect its allomeric function.
The purpose of this utility model is to provide a kind of lightweight flexible solar battery pack for solar powered aircraft for this reason.
For achieving the above object, the utility model is by the following technical solutions:
A kind of for the lightweight flexible solar battery pack on solar powered aircraft, it comprises from top to bottom the ETFE(ethylene-tetrafluoroethylene copolymer of bonding encapsulation successively) light-transmissive film, EVA(ethylene-vinyl acetate copolymer) layer, monocrystalline silicon piece and TPE(thermoplastic elastomer (TPE)) backboard; The thickness of described ETFE light-transmissive film is 40-60 μ m, and the thickness of described EVA layer is 220-300 μ m, and the thickness of described monocrystalline silicon piece is 100-160 μ m, and the thickness of described TPE backboard is 300-360 μ m.
The thickness of described ETFE light-transmissive film is 50 μ m.
The thickness of described EVA layer is 300 μ m.
The thickness of described monocrystalline silicon piece is 160 μ m.
The thickness of described TPE backboard is 350 μ m.
The beneficial effects of the utility model
:
1. the utility model solar module is ETFE light-transmissive film, EVA layer, monocrystalline silicon piece and the TPE backboard that bonds successively from top to bottom and encapsulate, and the thickness of ETFE light-transmissive film is 40-60 μ m, the thickness of EVA layer is 220-300 μ m, and the thickness of TPE backboard is 300-360 μ m.Make light-transmissive film and the thickness that reduces EVA layer by adopting ETFE material, the autologous density of the utility model solar module reduces much compared with the density of conventional solar cell assembly, significantly reduce the own wt that unit are too can battery component, and then can make the solar powered aircraft can carry more mission payload; In addition, adopt the ETFE material of suitable thickness to make light-transmissive film, and reduce the thickness of EVA layer, also can reduce restoring force and internal stress after the bending of the utility model solar module appropriateness, and then improve the attaching performance of solar module in fuselage, aerofoil surface, be suitable for large area monoblock and install.
2. the upper surface of the ETFE light-transmissive film of solar module of the present utility model adopts embossing processing, can further strengthen the tightness degree between each layer of whole solar module, and then the reliability of raising solar module.
Brief description of the drawings
For the content that makes utility model is more likely to be clearly understood, according to specific embodiment of the utility model also by reference to the accompanying drawings, the utility model is described in further detail, wherein below
Fig. 1 is the structural representation of solar energy crystal silicon battery component package scheme of the present utility model.
In figure, Reference numeral is expressed as:
1-ETFE light-transmissive film; 2-EVA layer; 3-monocrystalline silicon piece; 4-TPE backboard.
Embodiment
Embodiment 1
Referring to Fig. 1, lightweight flexible solar battery pack of the present utility model, it comprises from top to bottom ETFE light-transmissive film 1, EVA layer 2, monocrystalline silicon piece 3 and the TPE backboard 4 of bonding encapsulation successively.Laminating apparatus of the present utility model can directly use existing dull and stereotyped ETFE light-transmissive film lamination of solar battery components equipment on market, and without other higher technical requirement, therefore can additionally not increase cost.
In present embodiment, the thickness of described ETFE light-transmissive film 1 is 50 μ m, and the thickness of described EVA layer 2 is 300 μ m, and the thickness of described TPE backboard 4 is 350 μ m, and the thickness of described monocrystalline silicon piece 3 is 160 μ m.The surface density of this preferred version made solar module is out 1.23kg/m
2, to compare and the lamination scheme of traditional solar module, its surface density reduces 46% left and right.Suppose that the solar-electricity pool area that aircraft surfaces is laid is 3.5 m
2only solar module just can reduce 3.64kg left and right, concerning the very responsive Driven by Solar Energy aircraft of weight, can overcome less the gravity of 3.64kg or increase corresponding mission payload, and then make solar powered aircraft that more detecting devices can be installed, expand the performance of whole solar powered aircraft, if solar powered aircraft size is larger, photovoltaic module is Weight-optimised will be more remarkable.
In the present embodiment, in order to make upper surface ETFE light-transmissive film 1 lamination more reliable, table on it is carried out to embossing processing.For low speed low reynolds number solar powered aircraft, its wing, fuselage surface are low speed laminar flow, through wind tunnel test, embossing effects on surface aerodynamic effects is very little, therefore on the upper surface of ETFE light-transmissive film, carry out embossing processing and not only can not affect the flight stability of solar powered aircraft, can also increase the tightness degree of the each interlayer of solar module, improve security performance, increase the service life simultaneously.
For example, certain carbon fiber structural solar powered aircraft, requires total weight lower than 17kg, and low speed 10 ~ 20m/s cruises, and energy aspect adopts monocrystalline silicon assembly, and the test result that assembly is optimized front and back is as follows:
Before optimization: PET200 μ m+EVA500 μ m+ monocrystalline silicon piece 160 μ m+TPE backboard 350 μ m
After optimization: ETFE50 μ m+EVA300 μ m+ monocrystalline silicon piece 160 μ m+TPE backboard 350 μ m
Described ETFE light-transmissive film be upper surface through the ETFE of embossing processing film, the assembly gross area 1.93 ㎡, optimizing front assembly total weight is 4.38kg, surface density is 2.27kg/ ㎡ (assembly magnitude conventionally); After optimizing, assembly total weight is 2.37kg, and surface density is 1.228kg/ ㎡, and the pneumatic deflection in wind-tunnel measurements surface, close to 0, meets pneumatic index request.In this example visible, when the photovoltaic module after optimization meets aircraft utilization and requires, assembly weight saving approximately 46%, is the about 2kg of aircraft saving in weight, and this can carry the mission payload of 2kg for the less solar powered aircraft of global density more.
In present embodiment, the thickness of described ETFE light-transmissive film 1 is 40 μ m, and the thickness of described EVA layer 2 is 220 μ m, and the thickness of described monocrystalline silicon piece 3 is 150 μ m, and the thickness of described TPE backboard 4 is 300 μ m.
Embodiment 3
In present embodiment, the thickness of described ETFE light-transmissive film 1 is 60 μ m, the thickness of described EVA layer 2 is 250 μ m, the thickness of described TPE backboard 4 is 300 μ m, the thickness of described monocrystalline silicon piece 3 is 140 μ m, surface density is low to moderate 0.6kg/ ㎡, reduce 73.5%, and low speed air pressure deflection impacts hardly than traditional components weight to aircraft is pneumatic.
In other execution modes, according to practical situations, the thickness of described ETFE light-transmissive film 1 can be chosen as the arbitrary value between 40-60 μ m, the thickness of described EVA layer 2 is chosen as the arbitrary value between 220-300 μ m, the thickness of described TPE backboard 4 is chosen as the arbitrary value between 300-360 μ m, and the thickness of described monocrystalline silicon piece 3 is the arbitrary value between 100-160 μ m.As long as the one-tenth-value thickness 1/10 of above-mentioned each layer is chosen in above-mentioned scope, can make self surface density of the utility model solar module reduce much compared with the surface density of conventional solar cell assembly, and meet the dynamic pressure of general dopey covering and lower resistance requirement, significantly reduce the own wt of unit are crystal silicon solar batteries assembly, and then can make solar powered aircraft can be able to carry more other sniffer; In addition, this encapsulation scheme can also make the flexibility of whole solar module better, and after appropriateness bending, its restoring force and internal stress are all less, and then improves the attaching performance of solar module in fuselage, aerofoil surface.
Solar module of the present utility model has advantages of light weight, flexible, is particularly suitable for being installed on solar powered aircraft fuselage and wing; But it will be understood by those skilled in the art that solar module of the present utility model also can be installed on the equipment surface of other curved surface or plane, as solar telephone; In addition, solar module of the present utility model can also be made by mould the curved solar energy battery component of various shapes, as wing windward side, the excessive curved surface of Wing-Body Configurations etc.
Above-mentioned embodiment is just explained in detail the technical solution of the utility model; the utility model is not limited only to above-described embodiment; the above-mentioned principle of every foundation and the improvement of spirit on the utility model basis, substitute, all should be within protection range of the present utility model.
Claims (1)
1. for the lightweight flexible solar battery pack on solar powered aircraft, it comprises from top to bottom the ETFE light-transmissive film (1) of bonding encapsulation successively, EVA layer (2), monocrystalline silicon piece (3) and TPE backboard (4); It is characterized in that: the thickness of described ETFE light-transmissive film (1) is 40-60 μ m, the thickness of described EVA layer (2) is 220-300 μ m, and the thickness of described monocrystalline silicon piece (3) is 100-160 μ m, and the thickness of described TPE backboard (4) is 300-360 μ m.
2. according to claim 1 a kind of for the lightweight flexible solar battery pack on solar powered aircraft, it is characterized in that: the thickness of described ETFE light-transmissive film (1) is 50 μ m.
3. according to claim 2 a kind of for the lightweight flexible solar battery pack on solar powered aircraft, it is characterized in that: the thickness of described EVA layer (2) is 300 μ m.
4. according to claim 3 a kind of for the lightweight flexible solar battery pack on solar powered aircraft, it is characterized in that: the thickness of described monocrystalline silicon piece (3) is 160 μ m.
5. according to claim 4 a kind of for the lightweight flexible solar battery pack on solar powered aircraft, it is characterized in that: the thickness of described TPE backboard (4) is 350 μ m.
6. arbitrary described a kind of for the lightweight flexible solar battery pack on solar powered aircraft according to claim 1-5, it is characterized in that: described ETFE light-transmissive film (1) is for upper surface is through the ETFE of embossing processing film.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320848268.1U CN203659894U (en) | 2013-12-20 | 2013-12-20 | Lightweighting flexible solar cell assembly for solar airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320848268.1U CN203659894U (en) | 2013-12-20 | 2013-12-20 | Lightweighting flexible solar cell assembly for solar airplane |
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| Publication Number | Publication Date |
|---|---|
| CN203659894U true CN203659894U (en) | 2014-06-18 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320848268.1U Expired - Lifetime CN203659894U (en) | 2013-12-20 | 2013-12-20 | Lightweighting flexible solar cell assembly for solar airplane |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104890871A (en) * | 2015-06-23 | 2015-09-09 | 中国航空工业集团公司西安飞机设计研究所 | Solar drone and operating method thereof |
| CN105374890A (en) * | 2015-12-07 | 2016-03-02 | 上海空间电源研究所 | Thinning crystalline silica solar battery assembly structure applied to stratosphere airship |
| CN105680775A (en) * | 2014-11-18 | 2016-06-15 | 上海空间电源研究所 | Semi-flexible solar cell array for stratospheric airship |
| CN107871797A (en) * | 2017-11-30 | 2018-04-03 | 北京昶远科技有限公司 | A kind of HAE solar energy unmanned plane photovoltaic aerofoil and preparation method thereof |
| CN108075005A (en) * | 2017-11-29 | 2018-05-25 | 北京昶远科技有限公司 | It is a kind of for high-weatherability light flexible photovoltaic module of high altitude long time solar energy unmanned plane and preparation method thereof |
-
2013
- 2013-12-20 CN CN201320848268.1U patent/CN203659894U/en not_active Expired - Lifetime
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105680775A (en) * | 2014-11-18 | 2016-06-15 | 上海空间电源研究所 | Semi-flexible solar cell array for stratospheric airship |
| CN104890871A (en) * | 2015-06-23 | 2015-09-09 | 中国航空工业集团公司西安飞机设计研究所 | Solar drone and operating method thereof |
| CN104890871B (en) * | 2015-06-23 | 2017-03-08 | 中国航空工业集团公司西安飞机设计研究所 | A kind of solar energy unmanned plane and solar energy unmanned plane method of operating |
| CN105374890A (en) * | 2015-12-07 | 2016-03-02 | 上海空间电源研究所 | Thinning crystalline silica solar battery assembly structure applied to stratosphere airship |
| CN108075005A (en) * | 2017-11-29 | 2018-05-25 | 北京昶远科技有限公司 | It is a kind of for high-weatherability light flexible photovoltaic module of high altitude long time solar energy unmanned plane and preparation method thereof |
| CN107871797A (en) * | 2017-11-30 | 2018-04-03 | 北京昶远科技有限公司 | A kind of HAE solar energy unmanned plane photovoltaic aerofoil and preparation method thereof |
| CN107871797B (en) * | 2017-11-30 | 2023-10-13 | 北京昶远科技有限公司 | High-altitude long-endurance solar unmanned aerial vehicle photovoltaic airfoil and manufacturing method thereof |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| EE01 | Entry into force of recordation of patent licensing contract |
Assignee: DONGHAN SOLAR UAV TECHNOLOGY Co.,Ltd. Assignor: BEIJING HANERGY CHUANGYU S&T Co.,Ltd. Contract record no.: 2017990000025 Denomination of utility model: Lightweighting flexible solar cell assembly for solar airplane Granted publication date: 20140618 License type: Common License Record date: 20170118 |
|
| LICC | Enforcement, change and cancellation of record of contracts on the licence for exploitation of a patent or utility model | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 102209 Beijing city Changping District town Beiqijia Hongfu Pioneer Park No. 15 hospital Patentee after: BEIJING CHUANGYU TECHNOLOGY Co.,Ltd. Address before: 102209 Beijing city Changping District town Beiqijia Hongfu Pioneer Park No. 15 hospital Patentee before: BEIJING HANERGY CHUANGYU S&T Co.,Ltd. |
|
| CP01 | Change in the name or title of a patent holder | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 102209 Beijing city Changping District town Beiqijia Hongfu Pioneer Park No. 15 hospital Patentee after: DONGTAI HI-TECH EQUIPMENT TECHNOLOGY Co.,Ltd. Address before: 102209 Beijing city Changping District town Beiqijia Hongfu Pioneer Park No. 15 hospital Patentee before: DONGTAI HI-TECH EQUIPMENT TECHNOLOGY (BEIJING) Co.,Ltd. Address after: 102209 Beijing city Changping District town Beiqijia Hongfu Pioneer Park No. 15 hospital Patentee after: DONGTAI HI-TECH EQUIPMENT TECHNOLOGY (BEIJING) Co.,Ltd. Address before: 102209 Beijing city Changping District town Beiqijia Hongfu Pioneer Park No. 15 hospital Patentee before: Beijing Chuangyu Technology Co.,Ltd. |
|
| CP01 | Change in the name or title of a patent holder | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20210207 Address after: Unit 611, unit 3, 6 / F, building 1, yard 30, Yuzhi East Road, Changping District, Beijing 102208 Patentee after: Zishi Energy Co.,Ltd. Address before: 102209 Beijing city Changping District town Beiqijia Hongfu Pioneer Park No. 15 hospital Patentee before: DONGTAI HI-TECH EQUIPMENT TECHNOLOGY Co.,Ltd. |
|
| TR01 | Transfer of patent right | ||
| CX01 | Expiry of patent term |
Granted publication date: 20140618 |
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| CX01 | Expiry of patent term |