CN107871797B - High-altitude long-endurance solar unmanned aerial vehicle photovoltaic airfoil and manufacturing method thereof - Google Patents
High-altitude long-endurance solar unmanned aerial vehicle photovoltaic airfoil and manufacturing method thereof Download PDFInfo
- Publication number
- CN107871797B CN107871797B CN201711234815.6A CN201711234815A CN107871797B CN 107871797 B CN107871797 B CN 107871797B CN 201711234815 A CN201711234815 A CN 201711234815A CN 107871797 B CN107871797 B CN 107871797B
- Authority
- CN
- China
- Prior art keywords
- airfoil
- pressing
- pressing component
- photovoltaic
- protective film
- Prior art date
- 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.)
- Active
Links
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 32
- 239000000463 material Substances 0.000 claims abstract description 92
- 238000003825 pressing Methods 0.000 claims abstract description 72
- 230000001681 protective effect Effects 0.000 claims abstract description 27
- 239000000853 adhesive Substances 0.000 claims abstract description 26
- 238000002360 preparation method Methods 0.000 claims abstract description 26
- 230000001070 adhesive effect Effects 0.000 claims abstract description 25
- 239000011347 resin Substances 0.000 claims abstract description 15
- 229920005989 resin Polymers 0.000 claims abstract description 15
- 239000010410 layer Substances 0.000 claims abstract description 13
- 239000003292 glue Substances 0.000 claims abstract description 12
- 238000010030 laminating Methods 0.000 claims abstract description 8
- 239000002344 surface layer Substances 0.000 claims abstract description 8
- 238000000034 method Methods 0.000 claims description 10
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 6
- 229910052782 aluminium Inorganic materials 0.000 claims description 6
- 239000005341 toughened glass Substances 0.000 claims description 6
- 150000001875 compounds Chemical class 0.000 claims description 5
- -1 polytetrafluoroethylene Polymers 0.000 claims description 4
- 229920001343 polytetrafluoroethylene Polymers 0.000 claims description 4
- 239000004810 polytetrafluoroethylene Substances 0.000 claims description 4
- 238000001816 cooling Methods 0.000 claims description 3
- 238000005520 cutting process Methods 0.000 claims description 2
- 239000005357 flat glass Substances 0.000 claims description 2
- 239000012535 impurity Substances 0.000 abstract description 6
- 238000003860 storage Methods 0.000 abstract description 4
- 239000002131 composite material Substances 0.000 abstract description 3
- 238000005516 engineering process Methods 0.000 description 6
- 238000005056 compaction Methods 0.000 description 5
- 230000000694 effects Effects 0.000 description 4
- 239000004744 fabric Substances 0.000 description 4
- 238000013329 compounding Methods 0.000 description 3
- 239000002313 adhesive film Substances 0.000 description 2
- 230000003712 anti-aging effect Effects 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000005260 corrosion Methods 0.000 description 2
- 238000009517 secondary packaging Methods 0.000 description 2
- 238000007711 solidification Methods 0.000 description 2
- 230000008023 solidification Effects 0.000 description 2
- 239000013585 weight reducing agent Substances 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000005021 flexible packaging material Substances 0.000 description 1
- 239000003365 glass fiber Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000005286 illumination 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
- 238000005457 optimization Methods 0.000 description 1
- 238000012536 packaging technology Methods 0.000 description 1
- 230000002441 reversible effect Effects 0.000 description 1
- 238000003892 spreading 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
- H01L31/04—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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01L—SEMICONDUCTOR DEVICES NOT COVERED BY CLASS H10
- H01L31/00—Semiconductor devices sensitive to infrared radiation, light, electromagnetic radiation of shorter wavelength or corpuscular radiation and specially adapted either for the conversion of the energy of such radiation into electrical energy or for the control of electrical energy by such radiation; Processes or apparatus specially adapted for the manufacture or treatment thereof or of parts thereof; Details thereof
- H01L31/04—Semiconductor devices sensitive to infrared radiation, light, electromagnetic radiation of shorter wavelength or corpuscular radiation and specially adapted either for the conversion of the energy of such radiation into electrical energy or for the control of electrical energy by such radiation; Processes or apparatus specially adapted for the manufacture or treatment thereof or of parts thereof; Details thereof adapted as photovoltaic [PV] conversion devices
- H01L31/042—PV modules or arrays of single PV cells
- H01L31/048—Encapsulation of modules
- H01L31/0481—Encapsulation of modules characterised by the composition of the encapsulation material
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/50—Photovoltaic [PV] energy
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Condensed Matter Physics & Semiconductors (AREA)
- Electromagnetism (AREA)
- General Physics & Mathematics (AREA)
- Computer Hardware Design (AREA)
- Microelectronics & Electronic Packaging (AREA)
- Power Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Photovoltaic Devices (AREA)
Abstract
The invention discloses a high-altitude long-endurance solar unmanned aerial vehicle photovoltaic airfoil and a manufacturing method thereof, wherein the manufacturing method comprises the following steps: step one: horizontally arranging solar cells on a horizontal carrier plate, covering a layer of bonding material on the surface of the cells, and covering a transparent protective film on the surface of the bonding material to form a pre-pressing assembly preparation material; step two: placing the pre-pressing component preparation material into a laminating machine, and performing high-temperature vacuum pressing to form a pre-pressing component; step three: and taking the pre-pressing assembly as an airfoil surface layer, covering an airfoil material on the back surface, filling resin glue, and carrying out composite curing to form the photovoltaic airfoil. The back of the pre-pressing component is not provided with the adhesive material, and is the back of the whole array of solar cells, so that impurities are not adsorbed, and the requirement on the transportation, storage and secondary curing production environment of the pre-pressing component is low, thereby reducing the manufacturing cost.
Description
Technical Field
The invention belongs to the field of unmanned aerial vehicles, relates to airplane airfoil processing, and in particular relates to an airplane airfoil with a photovoltaic module and a manufacturing method thereof.
Background
The aircraft is limited by load, the cruising ability becomes a technical bottleneck of development, the application field of the aircraft is continuously expanded along with the continuous development of solar energy technology, and the solar energy is used as sustainable energy, and can be combined with the aircraft to greatly improve the cruising ability of the aircraft; however, most of the aircraft body is curved, and although flexible solar packaging technology exists at present, the aircraft body is still used in a planar state, and the technical field of curved surface formation of flexible solar components is still a large blank.
In the field of curved surface solar module manufacturing, a similar technical process is as follows: firstly typesetting the solar cell plane, attaching adhesive materials on two sides to pre-press to form pre-press assembly components with two sides being adhesive materials, respectively arranging curved plates on two sides of the pre-press assembly components as front and rear plates, and placing the front and rear plates into an autoclave to form the curved assembly components.
The prior art has the following defects:
1. the two sides of the pre-pressing assembly are both adhesive materials, the surfaces of the pre-pressing assembly are easy to adsorb various impurities and are not easy to remove, the adhesive materials have no rigidity and are extremely easy to denature, the transportation and storage requirements are extremely strict, and the secondary packaging requirements are ultra-clean environments;
2. if the flexible component adopts the technology, the flexible packaging material will be out of line and fold during secondary packaging;
3. the bonding material of the prior art scheme can only use reversible high-temperature bonding material;
4. the prior art is applied to the field of photovoltaic wing manufacturing, actual operation is difficult, and the weight of the wing is increased due to the existing manufacturing method of the pre-compression assembly
Related references: CN 102856410A.
Disclosure of Invention
The invention aims to solve the problems, and provides a high-altitude long-endurance solar unmanned aerial vehicle photovoltaic airfoil and a manufacturing method thereof, wherein an upper-layer prepressing component is firstly manufactured, an airfoil material is used as a backboard, and the technology of directly compounding the photovoltaic airfoil is adopted, and the prepressing component is structurally optimized, so that the photovoltaic component and the airfoil are compounded more simply and reasonably, the effects of quick production and weight reduction of the aircraft photovoltaic airfoil are achieved, and the solar unmanned aerial vehicle photovoltaic airfoil has the advantages of simplicity in manufacturing, low cost, light weight and the like, and is a great breakthrough of solar energy in the application field of the aircraft.
The utility model provides a long solar unmanned aerial vehicle photovoltaic airfoil of time of high altitude, includes solar cell, bonding material, transparent protection film, airfoil material, and solar cell one side passes through bonding material and connects transparent protection film, forms pre-compaction subassembly preparation material, and pre-compaction subassembly preparation material carries out vacuum pressing, forms pre-compaction subassembly, and solar cell's another side and airfoil material pass through resin glue compound solidification in the pre-compaction subassembly and are connected.
A method for manufacturing a photovoltaic airfoil of a high-altitude long-endurance solar unmanned aerial vehicle comprises the following steps:
step one: horizontally arranging solar cells on a horizontal carrier plate, covering a layer of bonding material on the surface of the cells, and covering a transparent protective film on the surface of the bonding material to form a pre-pressing assembly preparation material;
step two: placing the pre-pressing component preparation material into a laminating machine, and performing high-temperature vacuum pressing to form a pre-pressing component;
step three: and taking the pre-pressing assembly as an airfoil surface layer, covering an airfoil material on the back surface, filling resin glue, and carrying out composite curing to form the photovoltaic airfoil.
The invention has the advantages that:
(1) The back of the pre-pressing component is not provided with the adhesive material, and is the back of the whole array of solar cells, so that impurities are not adsorbed, the requirement on the transportation, storage and secondary curing production environment of the pre-pressing component is low, and the manufacturing cost is reduced;
(2) The whole pre-pressing assembly only uses one layer of bonding material, has thin thickness and light weight, reduces the weight of the whole airplane body, and improves the loading capacity and the cruising capacity;
(3) The surface of the invention is a transparent protective film, has good anti-aging and anti-corrosion effects, is not an adhesive surface, and therefore, does not adsorb impurities, and is directly used as the outermost surface of the photovoltaic airfoil of the aircraft, secondary processing is not needed, the manufacturing process is simplified, and the production cost is reduced;
(4) The pre-pressing component is formed by once curing the surface transparent protective film, so that the pre-pressing component has high flexibility, and the phenomenon of line outgoing wrinkling between the flexible transparent protective film and the adhesive film caused by secondary line outgoing curing is avoided;
(5) According to the invention, the wing material is used as the film of the pre-pressing component, the resin adhesive used for wing molding is used as the adhesive between the film and the pre-pressing component, so that the use amount of the adhesive is minimized, the weight is minimized, and the material process is more suitable for manufacturing the aircraft wing and is simple to operate.
Drawings
FIG. 1 is a schematic illustration of the preparation of material for a precompaction assembly of the present invention;
FIG. 2 is a schematic view of the precompression assembly of the present invention;
FIG. 3 is a schematic illustration of the fabrication of a photovoltaic airfoil of the present invention;
FIG. 4 is a schematic view of a photovoltaic airfoil of the present invention;
in the figure:
1-transparent protective film 2-adhesive material 3-solar cell
4-carrier 5-pre-pressing assembly 6-resin adhesive
7-wing Material 8-light Fu Yimian
Detailed Description
The invention will be described in further detail with reference to the drawings and examples.
The invention relates to a photovoltaic airfoil of a solar unmanned aerial vehicle with high altitude and long endurance, which comprises a solar cell 3, an adhesive material 2, a transparent protective film 1 and a wing material 7, wherein one surface of the solar cell 3 is connected with the transparent protective film 1 through the adhesive material 2 to form a pre-pressing assembly preparation material, the pre-pressing assembly preparation material is subjected to vacuum pressing to form a pre-pressing assembly 5, and the other surface of the solar cell 3 in the pre-pressing assembly 5 is in compound curing connection with the wing material 7 through resin glue 6.
The solar cell 3 is connected and fixed on the horizontal carrier plate 4, positive and negative bus bars are led out and fixed to form a solar cell array module, the solar cell array module is connected with the transparent protective film 1 through the bonding material 2, and the four sides of the bonding material 2 and the transparent protective film 1 are larger than those of the solar cell array module to form a pre-pressing assembly preparation material.
The preparation material of the pre-pressing assembly is subjected to high-temperature vacuum pressing through a laminating machine, is taken down from the carrier plate 4 after being cooled, and is cut around to form the pre-pressing assembly 5.
The protective film in the pre-pressing assembly 5 is set as an airfoil surface layer, resin glue is filled between the other surface of the protective film and the airfoil material 7, and the protective film is integrally cured through an autoclave to form the photovoltaic airfoil 8.
The invention relates to a method for manufacturing a photovoltaic airfoil of a solar unmanned aerial vehicle at high altitude and long endurance, which comprises the following steps:
step 1: horizontally arranging solar cells on a horizontal carrier plate, covering a layer of bonding material on the surface of the cells, and covering a transparent protective film on the surface of the bonding material to form a pre-pressing assembly preparation material;
the horizontal carrier plate is made by covering high temperature cloth (polytetrafluoroethylene) on a planar aluminum plate or toughened glass and mutually fixing the two plates; the solar cells are connected in series and parallel according to the design, are fixed on high-temperature cloth of a horizontal carrier plate, lead out positive and negative bus bars and are fixed to form a solar cell array module; covering a layer of bonding material on the surface of the solar cell array module, wherein the four-side size of the bonding material is larger than that of the solar cell array module; covering a transparent protective film on the adhesive material, wherein the four sides of the transparent protective film are larger than the four sides of the adhesive material; forming a pre-pressed assembly preparation material;
step 2: placing the pre-pressing component preparation material into a laminating machine, and performing high-temperature vacuum pressing to form a pre-pressing component;
horizontally placing the preparation material of the pre-pressing assembly into a laminating machine, carrying out high-temperature vacuum pressing, taking out after cooling, taking down the preparation material from the carrier plate, cutting the periphery, and removing redundant rim charge to form the pre-pressing assembly; the pre-pressing assembly is characterized in that: the back surface is not provided with an adhesive material, and is the back surface of the solar cell array; the whole pre-pressing assembly only uses one layer of bonding material, and has thin thickness and light weight; the surface is a transparent protective film, has good anti-aging and anti-corrosion effects, is not an adhesive surface, does not adsorb impurities, is directly used as the outermost surface of the photovoltaic airfoil of the airplane, and does not need secondary processing.
Step 3: taking the pre-pressing assembly as an airfoil surface layer, covering an airfoil material on the back surface, filling resin glue, and carrying out composite curing to form a photovoltaic airfoil 8 used by a final aircraft;
the prepressing assembly is used as an airfoil surface layer (the surface provided with a transparent protective film is the surface layer), the back surface is covered with an airfoil material, resin glue is filled, and the airfoil material is put into an autoclave for integral curing to prepare the photovoltaic airfoil 8 used by the final aircraft.
The invention adopts the technology of firstly manufacturing the upper layer pre-pressing component, taking the airfoil material as the backboard and directly compounding the airfoil material into the photovoltaic airfoil, and the structure of the pre-pressing component is optimized, so that the compounding of the photovoltaic component and the airfoil is simpler and more reasonable, the effects of quick production and weight reduction of the photovoltaic airfoil of the airplane are achieved, the advantages of simple manufacture, low cost, light weight and the like are achieved, and the invention is a great breakthrough of solar energy in the application field of the airplane.
Examples:
the invention discloses a method for manufacturing a photovoltaic airfoil of a high-altitude long-endurance solar unmanned aerial vehicle, which comprises the following steps:
step 1: as shown in fig. 1, solar cells 3 are horizontally arranged on a horizontal carrier plate 4, a layer of adhesive material 2 is covered on the surface of the cells 3, and a transparent protective film 1 is covered on the surface of the adhesive material 2 to form a pre-pressing assembly preparation material.
Step 2: the pre-press assembly preparation material is placed into a laminator and high temperature vacuum pressed to form a pre-press assembly 5, as shown in fig. 2.
Step 3: as shown in fig. 3, the pre-compression assembly 5 is used as an airfoil surface layer, the back surface is covered with an airfoil material 7, and the resin glue 6 is filled for compound curing to form a photovoltaic airfoil 8 used by the final aircraft, as shown in fig. 4.
The horizontal carrier plate 4 has the structure that: spreading a layer of high-temperature cloth (polytetrafluoroethylene) on a 5mm aluminum plate or a toughened glass plate, wherein the aluminum plate or the toughened glass is adopted, so that the temperature of a bottom plate of the laminating machine can be rapidly conducted to prepare a pre-pressing component preparation material, and the bonding material is melted by heating; because the aluminum plate and the toughened glass have rigidity and small thermal expansion coefficients, the battery plate array is not deviated due to deformation in the carrying process; the laying of the high-temperature cloth is to place the bonding material to bond with the aluminum plate or the toughened glass, so that the pre-pressing assembly cannot be taken down.
The surface transparent protective film is formed by the pre-pressing component through one-step curing, so that the pre-pressing component has high flexibility, and the phenomenon of line outgoing wrinkling between the flexible transparent protective film and the adhesive film caused by line outgoing secondary curing is avoided.
The back of the pre-pressing component is not provided with an adhesive material, and is the back of the whole array of solar cells, so that impurities are not adsorbed, and the requirements on the transportation, storage and secondary curing production environment of the pre-pressing component are low, thereby reducing the manufacturing cost.
The wing material is flexible before solidification, usually glass fiber or carbon fiber and the like, is put into a mould after being filled with resin glue and solidified at high temperature and high pressure to form a certain rigid wing model, step 3, the wing surface material is replaced by a prepressing component, the wing material (flexibility) is still used on the back surface, and is put into the mould to be solidified at high temperature after being filled with the resin glue to obtain the photovoltaic wing model with a solar cell, and the photovoltaic wing model is different from the traditional curved surface component manufacturing method (the wing material is solidified and molded and is compounded with a prefabricated component). The back plate is made of wing materials, so that the whole wing can keep original rigidity, and the surface of the wing is provided with the pre-pressing assembly, so that the wing surface can generate electric energy through illumination, and the aircraft can be provided with the pre-pressing assembly. The method has the advantages of minimum resin glue amount and minimum weight of the manufactured wing.
The method for manufacturing the photovoltaic airfoil of the high-altitude long-endurance solar unmanned aerial vehicle is a novel technology combining solar energy with an airplane, and the photovoltaic airfoil with light weight and simple processing can be obtained through the method. Through the structural optimization of pre-compaction subassembly, can greatly reduced the preparation degree of difficulty and processing cost. The invention is more fit for the aircraft processing technology, the manufacture is simpler, and the yield is higher.
Claims (1)
1. A method for manufacturing a photovoltaic airfoil of a solar unmanned aerial vehicle for high altitude long endurance comprises the steps of, a solar cell (3), a carrier plate (4) and a wing material (7);
the solar cells (3) are connected in series and parallel according to the design, are fixed on polytetrafluoroethylene of the horizontal carrier plate (4), lead out positive and negative bus bars and are fixed to form a solar cell array module;
the manufacturing method is characterized by comprising the following steps:
step one: horizontally arranging solar cells (3) on a horizontal carrier plate (4), covering a layer of bonding material (2) on the surface of the solar cells (3), and covering a transparent protective film (1) on the surface of the bonding material (2) to form a pre-pressing assembly preparation material;
the horizontal carrier plate (4) is made by covering polytetrafluoroethylene on a planar aluminum plate or toughened glass and mutually fixing;
covering a layer of bonding material (2) on the surface of the solar cell array module, wherein the four-side size of the bonding material is larger than the four-side size of the solar cell array module; covering a transparent protective film (1) on the adhesive material (2), wherein the four sides of the transparent protective film are larger than the four sides of the adhesive material; forming a pre-pressed assembly preparation material;
step two: placing the pre-pressing assembly preparation material into a laminating machine, pressing at high temperature under vacuum, cooling, taking off the support plate, and cutting the periphery to form a pre-pressing assembly (5); in the second step, the pre-pressing component preparation material is horizontally placed into a laminating machine, high-temperature vacuum pressing is carried out, the pre-pressing component is taken out after cooling, the pre-pressing component is taken down from a carrier plate (4), the periphery of the pre-pressing component is cut, and redundant rim charge is removed, so that a pre-pressing component (5) is formed;
step three: taking the pre-pressing component (5) as an airfoil surface layer, filling resin glue (6) between the other surface and the airfoil material (7), and forming a photovoltaic airfoil (8) through integral compound curing of an autoclave; the back of the pre-pressing component (5) is not provided with an adhesive material, and is the back of the whole array of solar cells; the whole pre-pressing assembly (5) only uses one layer of bonding material (2), the surface is a transparent protective film (1), and the transparent protective film is directly used as the outermost surface of the plane light Fu Yimian (8), and secondary processing is not needed;
in the prepared high-altitude long-endurance solar unmanned aerial vehicle photovoltaic airfoil, one side of a solar cell (3) is connected with a transparent protective film (1) through an adhesive material (2) to form a pre-pressing assembly preparation material; the preparation material of the pre-pressing component is subjected to vacuum pressing to form a pre-pressing component (5) on the carrier plate (4); the other side of the solar cell (3) in the pre-pressing component (5) is in compound curing connection with the wing material (7) through the resin adhesive (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711234815.6A CN107871797B (en) | 2017-11-30 | 2017-11-30 | High-altitude long-endurance solar unmanned aerial vehicle photovoltaic airfoil and manufacturing method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711234815.6A CN107871797B (en) | 2017-11-30 | 2017-11-30 | High-altitude long-endurance solar unmanned aerial vehicle photovoltaic airfoil and manufacturing method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107871797A CN107871797A (en) | 2018-04-03 |
| CN107871797B true CN107871797B (en) | 2023-10-13 |
Family
ID=61755058
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711234815.6A Active CN107871797B (en) | 2017-11-30 | 2017-11-30 | High-altitude long-endurance solar unmanned aerial vehicle photovoltaic airfoil and manufacturing method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107871797B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110491960B (en) * | 2019-07-08 | 2021-10-15 | 上海空间电源研究所 | Pasting method of solar cell array and solar cell array manufactured by pasting method |
| CN113809193A (en) * | 2021-08-25 | 2021-12-17 | 常州亚玛顿股份有限公司 | Curved surface photovoltaic assembly and preparation method thereof |
| CN115522844B (en) * | 2022-09-30 | 2024-05-14 | 成都飞机工业（集团）有限责任公司 | Method for preventing surface of aircraft composite cabin door from being de-bonded with rubber |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101132031A (en) * | 2007-07-18 | 2008-02-27 | 厦门冠宇科技有限公司 | Manufacturing method for flexible solar cell unit |
| CN101777434A (en) * | 2010-03-12 | 2010-07-14 | 华中科技大学 | Encapsulating method for all-solid-state dye-sensitized solar cell |
| CN102386334A (en) * | 2011-11-24 | 2012-03-21 | 深圳市创益科技发展有限公司 | Solar cell photovoltaic building component and manufacturing method thereof |
| CN102760792A (en) * | 2012-06-18 | 2012-10-31 | 江苏核新太阳能电力有限公司 | Dry method packaging process of solar cell panel with rigid back plate |
| CN103715298A (en) * | 2013-12-18 | 2014-04-09 | 北京汉能创昱科技有限公司 | Curved-surface solar module manufacturing method |
| CN203659894U (en) * | 2013-12-20 | 2014-06-18 | 北京汉能创昱科技有限公司 | Lightweighting flexible solar cell assembly for solar airplane |
| CN105810776A (en) * | 2014-12-31 | 2016-07-27 | 北京汉能创昱科技有限公司 | Preparation method of carbon fiber solar panel and carbon fiber solar panel thereof |
| CN207474482U (en) * | 2017-11-30 | 2018-06-08 | 北京昶远科技有限公司 | A kind of high altitude long time solar energy unmanned plane photovoltaic aerofoil |
-
2017
- 2017-11-30 CN CN201711234815.6A patent/CN107871797B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101132031A (en) * | 2007-07-18 | 2008-02-27 | 厦门冠宇科技有限公司 | Manufacturing method for flexible solar cell unit |
| CN101777434A (en) * | 2010-03-12 | 2010-07-14 | 华中科技大学 | Encapsulating method for all-solid-state dye-sensitized solar cell |
| CN102386334A (en) * | 2011-11-24 | 2012-03-21 | 深圳市创益科技发展有限公司 | Solar cell photovoltaic building component and manufacturing method thereof |
| CN102760792A (en) * | 2012-06-18 | 2012-10-31 | 江苏核新太阳能电力有限公司 | Dry method packaging process of solar cell panel with rigid back plate |
| CN103715298A (en) * | 2013-12-18 | 2014-04-09 | 北京汉能创昱科技有限公司 | Curved-surface solar module manufacturing method |
| CN203659894U (en) * | 2013-12-20 | 2014-06-18 | 北京汉能创昱科技有限公司 | Lightweighting flexible solar cell assembly for solar airplane |
| CN105810776A (en) * | 2014-12-31 | 2016-07-27 | 北京汉能创昱科技有限公司 | Preparation method of carbon fiber solar panel and carbon fiber solar panel thereof |
| CN207474482U (en) * | 2017-11-30 | 2018-06-08 | 北京昶远科技有限公司 | A kind of high altitude long time solar energy unmanned plane photovoltaic aerofoil |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107871797A (en) | 2018-04-03 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103332290B (en) | A kind of wing structure-solar cell integral module and method of production thereof | |
| CN101685838B (en) | Photovoltaic component and manufacturing method thereof | |
| CN107871797B (en) | High-altitude long-endurance solar unmanned aerial vehicle photovoltaic airfoil and manufacturing method thereof | |
| CN106299002B (en) | Flexible solar cell component and its preparation method and application | |
| CN103715298B (en) | Curved solar energy assembly manufacture method | |
| CN104210647A (en) | Wing structure-meshed solar wing design and development scheme | |
| CN105322039A (en) | Ultra-light flexible crystalline silicon solar cell module and preparation method thereof | |
| CN106379516B (en) | Solar powered aircraft wing and its manufacturing method | |
| CN104229120A (en) | Solar wing structure of aircraft based on photothermal integrated composite energy | |
| CN105810776A (en) | Preparation method of carbon fiber solar panel and carbon fiber solar panel thereof | |
| CN106449819B (en) | A kind of flexible solar cell component and its preparation method and application | |
| CN101719523B (en) | Solar energy battery panel for automobile | |
| CN101826577A (en) | Manufacturing method of plastic sealed solar photovoltaic assembly | |
| CN201523015U (en) | Plastic package solar energy photovoltaic component | |
| CN108831944A (en) | Solar vehicle assembly, preparation method thereof and vehicle | |
| CN207474482U (en) | A kind of high altitude long time solar energy unmanned plane photovoltaic aerofoil | |
| CN102431255A (en) | Composite material having solar cell and production method thereof | |
| CN108155259B (en) | Isolation film technology for stacking glass for photovoltaic module | |
| CN105185852B (en) | The flexible solar battery pack and its preparation technology of aramid fiber support | |
| CN111261739B (en) | Ultra-light flexible thin film solar cell module for near space airship | |
| CN209119132U (en) | Solar vehicle component and vehicle | |
| CN209071353U (en) | A kind of high CTM photovoltaic module of black silion cell | |
| CN209328917U (en) | Adjustable photovoltaic module press box | |
| CN206697496U (en) | The solar cell chunk of flexible package in a kind of solar energy unmanned plane | |
| WO2020037824A1 (en) | Solar vehicle component and preparation method therefor, and vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |