CN113327993A - High-output-voltage flexible thin-film solar cell module for near space aircraft - Google Patents
High-output-voltage flexible thin-film solar cell module for near space aircraft Download PDFInfo
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- CN113327993A CN113327993A CN202110569805.8A CN202110569805A CN113327993A CN 113327993 A CN113327993 A CN 113327993A CN 202110569805 A CN202110569805 A CN 202110569805A CN 113327993 A CN113327993 A CN 113327993A
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- solar cell
- output voltage
- flexible thin
- module
- thin film
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- 239000010409 thin film Substances 0.000 title claims abstract description 26
- 238000002955 isolation Methods 0.000 claims abstract description 11
- 229910000679 solder Inorganic materials 0.000 claims abstract description 8
- BQCADISMDOOEFD-UHFFFAOYSA-N Silver Chemical group [Ag] BQCADISMDOOEFD-UHFFFAOYSA-N 0.000 claims abstract description 7
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 claims description 5
- 229910052710 silicon Inorganic materials 0.000 claims description 5
- 239000010703 silicon Substances 0.000 claims description 5
- JBRZTFJDHDCESZ-UHFFFAOYSA-N AsGa Chemical compound [As]#[Ga] JBRZTFJDHDCESZ-UHFFFAOYSA-N 0.000 claims description 3
- 229910001218 Gallium arsenide Inorganic materials 0.000 claims description 3
- 239000004642 Polyimide Substances 0.000 claims description 3
- 239000000853 adhesive Substances 0.000 claims description 3
- 230000001070 adhesive effect Effects 0.000 claims description 3
- 238000005452 bending Methods 0.000 claims description 3
- 229920001721 polyimide Polymers 0.000 claims description 3
- 230000009286 beneficial effect Effects 0.000 abstract description 3
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
Images
Classifications
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- 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
- H01L31/044—PV modules or arrays of single PV cells including bypass diodes
- H01L31/0443—PV modules or arrays of single PV cells including bypass diodes comprising bypass diodes integrated or directly associated with the devices, e.g. bypass diodes integrated or formed in or on the same substrate as the photovoltaic 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
-
- 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
- H01L31/05—Electrical interconnection means between PV cells inside the PV module, e.g. series connection of PV cells
- H01L31/0504—Electrical interconnection means between PV cells inside the PV module, e.g. series connection of PV cells specially adapted for series or parallel connection of solar cells in a module
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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
Abstract
A high output voltage flexible thin film solar cell module for a near space aircraft, comprising: solar cell cluster, isolation diode module, fixed transparent insulating sticky tape, flexible interconnection horizontal bar and draw forth the solder strip, wherein, a plurality of the solar cell cluster set up in on the fixed transparent insulating sticky tape, keep apart the diode module paste in on the terminal silver foil of drawing forth of solar cell cluster, it is adjacent the solar cell cluster passes through flexible interconnection horizontal bar is in series and passes through draw forth solder strip parallel output. The application has the following beneficial effects: in the laying area with small rib spacing, the output voltage of a single solar cell module can reach more than 100V, so that the application advantage is expanded; high voltage output is formed without series connection of multiple components, so that the design difficulty of a solar cell array with high output voltage and laid on a curved surface is reduced; the maximum voltage difference between adjacent solar cell strings is within 80V, so that the electrostatic protection requirement is met, and the safety and reliability of the solar cell array are improved.
Description
Technical Field
The invention belongs to the technical field of photovoltaic power generation, and particularly relates to a high-output-voltage flexible thin-film solar cell module for an aircraft in a near space.
Background
The flexible thin film solar cell module has the characteristics of light weight, high flexibility, high efficiency and the like, and is widely applied to the solar unmanned aerial vehicle in the near space. Generally, in order to increase the rotation speed of the motor during high-altitude flight, the output voltage of the solar cell array is required to be over 100V. However, the output voltage of the solar cell module designed in the past is generally between 50 and 80V, so that the use requirement is difficult to meet, and the power of the aircraft is greatly reduced.
The main reasons why high output voltage cannot be realized at present are as follows:
(1) the rib spacing for laying the flexible thin film solar cell module is generally less than 500mm due to the structural strength limitation of the solar unmanned aerial vehicle, and the single cell string is difficult to realize the series connection of 35 or more cells, namely the 100V voltage output through the single cell string is difficult to realize;
(2) in order to increase the area of the flexible thin film solar cell module, the string pitch of the cell strings is generally designed to be 1mm, and under the condition of such small string pitch, electrostatic damage or self-discharge damage occurs at a high probability on the electrodes between adjacent cell strings with a voltage difference of more than 100V;
(3) the solar cell module region of the solar unmanned aerial vehicle capable of being paved is generally a curved surface, the generated currents of the solar cell modules positioned at different curvature radiuses have large difference, and the difficulty coefficient of the cross-rib position for serial design of the modules is extremely large.
Disclosure of Invention
In order to solve the above problems, the present invention provides a high output voltage flexible thin film solar cell module for an aircraft in a near space, comprising: solar cell cluster, isolation diode module, fixed transparent insulating sticky tape, flexible interconnection horizontal bar and draw forth the solder strip, wherein, a plurality of the solar cell cluster set up in on the fixed transparent insulating sticky tape, keep apart the diode module paste in on the terminal silver foil of drawing forth of solar cell cluster, it is adjacent the solar cell cluster passes through flexible interconnection horizontal bar is in series and passes through draw forth solder strip parallel output.
Preferably, the solar cell string comprises a plurality of solar cells connected in series, and a bypass diode module is arranged on the back surface of each solar cell.
Preferably, the adjacent solar cells are connected through an interconnection adhesive.
Preferably, adjacent solar cells are electrically connected through an interconnection sheet.
Preferably, the spacing between adjacent solar cell strings is 0.8mm-1.0 mm.
Preferably, the solar cell is a fully flexible thin film gallium arsenide solar cell with the maximum bending radius ranging from 5cm to 10 cm.
Preferably, the interconnection sheet is an interconnection silver foil having a thickness in the range of 30 μm to 60 μm.
Preferably, the bypass diode module is a GaInP bypass diode or a silicon-based bypass diode, the total thickness of the bypass diode module is 145 μm-180 μm, and the reverse voltage tolerance range of the single bypass diode module is 6V-10V.
Preferably, the isolation diode module is a silicon-based isolation diode with reverse voltage resistance ranging from 100V to 200V.
Preferably, the fixed transparent insulating tape is a polyimide tape having a thickness ranging from 10 μm to 30 μm.
The application provides a close on flexible thin film solar module of high output voltage for space aircraft has following beneficial effect:
(1) in the laying area with small rib spacing, the output voltage of a single solar cell module can reach more than 100V, so that the application advantage is expanded;
(2) high voltage output is formed without series connection of multiple components, so that the design difficulty of a solar cell array with high output voltage and laid on a curved surface is reduced;
(3) the maximum voltage difference between adjacent solar cell strings is within 80V, so that the electrostatic protection requirement is met, and the safety and reliability of the solar cell array are improved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is a schematic front view of a high output voltage flexible thin film solar cell module for a near space aircraft according to the present invention;
fig. 2 is a schematic diagram of a back side of a high-output voltage flexible thin-film solar cell module for an adjacent space aircraft according to the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in further detail with reference to the accompanying drawings in conjunction with the following detailed description. It should be understood that the description is intended to be exemplary only, and is not intended to limit the scope of the present invention. Moreover, in the following description, descriptions of well-known structures and techniques are omitted so as to not unnecessarily obscure the concepts of the present invention.
In an embodiment of the present application, as shown in fig. 1-2, the present invention provides a high output voltage flexible thin film solar cell module for a near space aircraft, comprising: solar cell cluster 1, isolation diode module 6, fixed transparent insulating tape 7, flexible interconnection horizontal bar 8 and draw forth solder strip 9, wherein, a plurality of solar cell cluster 1 set up in on the fixed transparent insulating tape 7, isolation diode module 6 paste in on the terminal silver foil of drawing forth of solar cell cluster 1, it is adjacent solar cell cluster 1 passes through flexible interconnection horizontal bar 8 establishes ties and passes through draw forth solder strip 9 parallel output.
In the embodiment of the application, the distance between adjacent solar cell strings 1 ranges from 1mm, the maximum voltage difference is 78V, and after two adjacent solar cell strings are connected in series, the output voltage of a single assembly reaches 156V.
As shown in fig. 1-2, in the embodiment of the present application, the solar cell string 1 includes a plurality of solar cells 2 connected in series, and a bypass diode module 5 is disposed on a back surface of each solar cell 2.
In the embodiment of the present application, as shown in fig. 1-2, adjacent solar cells 2 are connected by an interconnection adhesive 3. The interconnection paste 3 can realize physical connection between two adjacent solar cells 2.
As shown in fig. 1 to 2, in the embodiment of the present application, adjacent solar cells 2 are electrically connected to each other through a connection sheet 4. The interconnection sheet 4 may realize electrical connection between two adjacent solar cells 2.
In the embodiment of the application, the distance between the adjacent solar cell strings 1 is 0.8mm-1.0 mm.
In the embodiment of the application, the solar cell 2 is a fully flexible thin film gallium arsenide solar cell 2 with the maximum bending radius ranging from 5cm to 10 cm.
In the present embodiment, the interconnection sheet 4 is an interconnection silver foil having a thickness in the range of 30 μm to 60 μm.
In the embodiment of the present application, the bypass diode module 5 is a GaInP bypass diode or a silicon-based bypass diode, the total thickness of the bypass diode module 5 is 145 μm to 180 μm, and the reverse voltage tolerance range of the single bypass diode module 5 is 6V to 10V.
In the embodiment of the present application, the isolation diode module 6 is a silicon-based isolation diode with a reverse voltage tolerance range of 100V-200V.
In the embodiment of the present application, the fixed transparent insulating tape 7 is a polyimide tape having a thickness ranging from 10 μm to 30 μm.
The application provides a close on flexible thin film solar module of high output voltage for space aircraft has following beneficial effect:
(1) in the laying area with small rib spacing, the output voltage of a single solar cell module can reach more than 100V, so that the application advantage is expanded;
(2) high voltage output is formed without series connection of multiple components, so that the design difficulty of a solar cell array with high output voltage and laid on a curved surface is reduced;
(3) the maximum voltage difference between adjacent solar cell strings is within 80V, so that the electrostatic protection requirement is met, and the safety and reliability of the solar cell array are improved.
It is to be understood that the above-described embodiments of the present invention are merely illustrative of or explaining the principles of the invention and are not to be construed as limiting the invention. Therefore, any modification, equivalent replacement, improvement and the like made without departing from the spirit and scope of the present invention should be included in the protection scope of the present invention. Further, it is intended that the appended claims cover all such variations and modifications as fall within the scope and boundaries of the appended claims or the equivalents of such scope and boundaries.
Claims (10)
1. A high output voltage flexible thin film solar cell module for a near space aircraft, comprising: solar cell cluster, isolation diode module, fixed transparent insulating sticky tape, flexible interconnection horizontal bar and draw forth the solder strip, wherein, a plurality of the solar cell cluster set up in on the fixed transparent insulating sticky tape, keep apart the diode module paste in on the terminal silver foil of drawing forth of solar cell cluster, it is adjacent the solar cell cluster passes through flexible interconnection horizontal bar is in series and passes through draw forth solder strip parallel output.
2. The high-output voltage flexible thin film solar cell module for the near space aircraft as claimed in claim 1, wherein the solar cell string comprises a plurality of solar cells connected in series, and a bypass diode module is arranged on the back surface of each solar cell.
3. The high-output voltage flexible thin film solar cell module for the near space aircraft as claimed in claim 2, wherein adjacent solar cells are connected by an interconnection adhesive.
4. The high-output voltage flexible thin film solar cell module for an aircraft near space as claimed in claim 2, wherein adjacent solar cells are electrically connected by an interconnection sheet.
5. The high output voltage flexible thin film solar cell module for an adjacent space aircraft according to claim 1, wherein a pitch between adjacent solar cell strings is 0.8mm to 1.0 mm.
6. The high output voltage flexible thin film solar cell module for an adjacent space aircraft as claimed in claim 2, wherein the solar cell is a fully flexible thin film gallium arsenide solar cell having a maximum bending radius in the range of 5cm to 10 cm.
7. The high-output voltage flexible thin film solar cell module for a near space aircraft according to claim 4, wherein the interconnection sheet is an interconnection silver foil having a thickness in a range of 30 μm to 60 μm.
8. The high-output voltage flexible thin-film solar cell module for the near space aircraft as claimed in claim 2, wherein the bypass diode module is a GaInP bypass diode or a si-based bypass diode, the total thickness of the bypass diode module is 145 μm to 180 μm, and the reverse voltage resistance of the single bypass diode module is 6V to 10V.
9. The high-output voltage flexible thin-film solar cell module for the near space aircraft as claimed in claim 1, wherein the isolation diode module is a silicon-based isolation diode with a reverse voltage resistance ranging from 100V to 200V.
10. The high-output voltage flexible thin film solar cell module for the near space aircraft according to claim 1, wherein the fixed transparent insulating tape is a polyimide tape having a thickness in a range of 10 μm to 30 μm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110569805.8A CN113327993A (en) | 2021-05-25 | 2021-05-25 | High-output-voltage flexible thin-film solar cell module for near space aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110569805.8A CN113327993A (en) | 2021-05-25 | 2021-05-25 | High-output-voltage flexible thin-film solar cell module for near space aircraft |
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| CN113327993A true CN113327993A (en) | 2021-08-31 |
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| CN202110569805.8A Pending CN113327993A (en) | 2021-05-25 | 2021-05-25 | High-output-voltage flexible thin-film solar cell module for near space aircraft |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202259380U (en) * | 2011-10-11 | 2012-05-30 | 上海晶亨光电科技有限公司 | Solar cell assembly |
| CN106898665A (en) * | 2017-02-09 | 2017-06-27 | 北京四方创能光电科技有限公司 | A kind of tandem flexible thin-film solar cell component and preparation method thereof |
| CN109920873A (en) * | 2019-04-11 | 2019-06-21 | 青海黄河上游水电开发有限责任公司光伏产业技术分公司 | A kind of total bypass protection crystalline silicon solar cell modules |
| 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 |
| CN112289877A (en) * | 2020-10-30 | 2021-01-29 | 中国电子科技集团公司第十八研究所 | Bypass diode module for flexible thin film solar cell module |
| CN112825337A (en) * | 2019-11-21 | 2021-05-21 | 江苏宜兴德融科技有限公司 | Flexible solar cell array |
-
2021
- 2021-05-25 CN CN202110569805.8A patent/CN113327993A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202259380U (en) * | 2011-10-11 | 2012-05-30 | 上海晶亨光电科技有限公司 | Solar cell assembly |
| CN106898665A (en) * | 2017-02-09 | 2017-06-27 | 北京四方创能光电科技有限公司 | A kind of tandem flexible thin-film solar cell component and preparation method thereof |
| CN109920873A (en) * | 2019-04-11 | 2019-06-21 | 青海黄河上游水电开发有限责任公司光伏产业技术分公司 | A kind of total bypass protection crystalline silicon solar cell modules |
| CN112825337A (en) * | 2019-11-21 | 2021-05-21 | 江苏宜兴德融科技有限公司 | Flexible solar cell array |
| 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 |
| CN112289877A (en) * | 2020-10-30 | 2021-01-29 | 中国电子科技集团公司第十八研究所 | Bypass diode module for flexible thin film solar cell module |
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Effective date of registration: 20211123 Address after: 300384 No. 6 Huake No. 7 Road, Binhai New Area, Tianjin Binhai High-tech Industrial Development Zone Applicant after: The 18th Research Institute of China Electronics Technology Group Corporation Applicant after: CETC Energy Co.,Ltd. Address before: 300384 No. 6 Huake No. 7 Road, Binhai New Area, Tianjin Binhai High-tech Industrial Development Zone Applicant before: The 18th Research Institute of China Electronics Technology Group Corporation |
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Application publication date: 20210831 |