CN114257172A - Gallium arsenide solar cell array design method for solar unmanned aerial vehicle - Google Patents
Gallium arsenide solar cell array design method for solar unmanned aerial vehicle Download PDFInfo
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- 229910001218 Gallium arsenide Inorganic materials 0.000 title claims abstract description 85
- JBRZTFJDHDCESZ-UHFFFAOYSA-N AsGa Chemical compound [As]#[Ga] JBRZTFJDHDCESZ-UHFFFAOYSA-N 0.000 title claims abstract description 75
- 238000013461 design Methods 0.000 title claims abstract description 30
- 238000000034 method Methods 0.000 title claims abstract description 20
- 238000010248 power generation Methods 0.000 claims abstract description 37
- 239000000178 monomer Substances 0.000 claims abstract description 20
- 238000012360 testing method Methods 0.000 claims abstract description 10
- 210000004027 cell Anatomy 0.000 claims description 39
- 238000003466 welding Methods 0.000 claims description 8
- 238000006243 chemical reaction Methods 0.000 claims description 5
- 230000000712 assembly Effects 0.000 claims description 4
- 238000000429 assembly Methods 0.000 claims description 4
- 238000004519 manufacturing process Methods 0.000 claims description 4
- 210000003850 cellular structure Anatomy 0.000 claims description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000012544 monitoring process Methods 0.000 description 2
- 238000012795 verification Methods 0.000 description 2
- 238000003491 array Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 229910021419 crystalline silicon Inorganic materials 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000003475 lamination Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229910021421 monocrystalline silicon Inorganic materials 0.000 description 1
- 238000011160 research Methods 0.000 description 1
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02S—GENERATION OF ELECTRIC POWER BY CONVERSION OF INFRARED RADIATION, VISIBLE LIGHT OR ULTRAVIOLET LIGHT, e.g. USING PHOTOVOLTAIC [PV] MODULES
- H02S40/00—Components or accessories in combination with PV modules, not provided for in groups H02S10/00 - H02S30/00
- H02S40/30—Electrical components
- H02S40/34—Electrical components comprising specially adapted electrical connection means to be structurally associated with the PV module, e.g. junction boxes
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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
- H01L31/044—PV modules or arrays of single PV cells including bypass diodes
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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
- H01L31/05—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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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02S—GENERATION OF ELECTRIC POWER BY CONVERSION OF INFRARED RADIATION, VISIBLE LIGHT OR ULTRAVIOLET LIGHT, e.g. USING PHOTOVOLTAIC [PV] MODULES
- H02S40/00—Components or accessories in combination with PV modules, not provided for in groups H02S10/00 - H02S30/00
- H02S40/30—Electrical components
- H02S40/36—Electrical components characterised by special electrical interconnection means between two or more PV modules, e.g. electrical module-to-module connection
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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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- 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
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P70/00—Climate change mitigation technologies in the production process for final industrial or consumer products
- Y02P70/50—Manufacturing or production processes characterised by the final manufactured product
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Abstract
The invention relates to the technical field of solar unmanned aerial vehicles, and discloses a gallium arsenide solar cell array design method for a solar unmanned aerial vehicle. The operation steps comprise: the method comprises the following steps of gallium arsenide battery monomer type selection, component design, component testing and grading, power generation array division and power generation battery array confluence design. By the optimized design of the size of the component, the effective power generation area of the gallium arsenide battery on the unmanned aerial vehicle can be maximized; through the design that each string of batteries in the assembly is output with a positive series anti-reverse diode, the short-circuit fault of a single string of batteries can be effectively isolated; the assembly is segmented by the maximum power point voltage, the maximum power output of the gallium arsenide solar cell array can be realized, and the phenomenon of assembly matching failure is avoided. The design method of the unmanned aerial vehicle gallium arsenide solar cell array is easy to realize in engineering.
Description
Technical Field
The invention belongs to the technical field of solar unmanned aerial vehicles, and particularly relates to a gallium arsenide solar cell array design method for a solar unmanned aerial vehicle.
Background
The solar unmanned aerial vehicle takes solar energy as energy, can fly permanently in theory, has no pollution to the environment, is flexible to use, has low cost and has wide application prospect. The system can be used for atmospheric research, weather forecast, environment and disaster monitoring, crop remote measurement, traffic control, telecommunication and television service, natural protection area monitoring and the like in civil use; military applications can be used for border patrol, reconnaissance, communication relay and the like.
In consideration of the application characteristics of the solar unmanned aerial vehicle, the solar cell module not only has higher conversion efficiency, but also has the characteristics of light weight, flexibility, adaptability to the application of wing airfoil curved surfaces and the like. At the present stage, the solar unmanned aerial vehicle is mainly divided into a skin integrated unmanned aerial vehicle and a monocoque unmanned aerial vehicle according to different application modes of the solar cell module, and the two types of unmanned aerial vehicles respectively have advantages and disadvantages. After the solar cell modules are laid on the machine, a plurality of solar cell arrays are formed by series-parallel connection among the modules. The generated power and voltage range of the solar cell array need to be matched with a corresponding MPPT (maximum power point tracking) controller. The design of the solar cell array is crucial, and the maximum power output and the full-machine energy collection efficiency of the solar cell can be realized. The solar cell array on the unmanned aerial vehicle is designed by considering the influences of an airfoil curved surface, flight attitude and the like. At present, a solar unmanned aerial vehicle in a near space at home and abroad mainly carries a monocrystalline silicon battery component to carry out low-altitude flight verification. With the increasing demands of flying height, flying time and flight, the application of gallium arsenide battery components is one of the future development trends.
According to the verification, the current design method and reference experience of the gallium arsenide solar cell array of the solar unmanned aerial vehicle are few. Therefore, the invention provides a gallium arsenide solar cell array design method for a solar unmanned aerial vehicle.
Disclosure of Invention
The invention provides a gallium arsenide solar cell array design method for a solar unmanned aerial vehicle, which can effectively isolate the short-circuit fault of a single-string battery, realize the maximum power output and the full-machine energy collection efficiency and is easy to realize in engineering.
The invention discloses a gallium arsenide solar cell array design method of a solar unmanned aerial vehicle, which comprises the following steps:
selecting a gallium arsenide battery monomer, namely selecting the gallium arsenide battery monomer according to the size of the wing, the conversion efficiency and the cost requirement, and determining the size, the maximum power point voltage and the maximum power of the gallium arsenide battery monomer;
designing a gallium arsenide battery assembly, namely determining the serial number of gallium arsenide battery monomers according to the input and output voltage requirement of an MPPT controller; determining the specifications of a standard gallium arsenide battery component and a non-standard gallium arsenide battery component; determining the gaps between monomers in the gallium arsenide cell component in the serial direction and the parallel direction according to the effective power generation area and the production process requirement; the positive electrode output of each battery in the gallium arsenide battery component is connected with an anti-reverse diode in series; the positive electrode and the negative electrode output in each serial direction in the assembly are connected in parallel through a confluence welding strip to form a positive electrode and a negative electrode of the assembly;
testing and grading the gallium arsenide battery assembly, namely testing a current-voltage curve of the assembly in a standard environment, and grading according to the maximum power point working voltage value of the assembly;
a gallium arsenide cell power generation array dividing step, namely extracting wing profiles, and determining the number of components in the power generation array along the chord length direction according to the curve length of the wing surfaces on the wings; determining the number of components along the wingspan direction according to the MPPT controller power corresponding to the power generation array; according to the grading result, the maximum power point working voltage value of the gallium arsenide battery pack in the same power generation array is required to be in the same grade;
and (3) gallium arsenide power generation array confluence design, wherein all gallium arsenide battery assemblies in the same power generation array are connected in parallel through confluence welding strips, and the positive and negative electrodes of the power generation array are led out and connected into corresponding MPPT controllers.
Furthermore, in the design step of the gallium arsenide battery pack, the gap required in the serial connection direction is controlled between 0mm and 1 mm; the parallel connection direction requires the gap to be controlled between 0.5mm and 1 mm; the thickness of the diode is not more than 1.2 mm; the width of the blank in the serial direction in the module is not more than 8mm, and the width of the blank in the parallel direction is not more than 3 mm.
Furthermore, in the gallium arsenide battery assembly test and grading, the interval between grading voltages is 1V.
Furthermore, in the division of the gallium arsenide cell power generation array, the distance between the component and the front edge of the wing profile is 20-50 mm, and the distance between the component and the rear edge of the wing profile is 10-30 mm; the distance between the components is 1 mm.
The invention solves the problem that the gallium arsenide single battery is applied to the unmanned aerial vehicle due to high voltage and small size. By the optimized design of the size of the component, the effective power generation area of the gallium arsenide battery on the unmanned aerial vehicle can be maximized; through the design that each string of batteries in the assembly is output with a positive series anti-reverse diode, the short-circuit fault of a single string of batteries can be effectively isolated; the assembly is segmented by the maximum power point voltage, the maximum power output of the gallium arsenide solar cell array can be realized, and the phenomenon of assembly matching failure is avoided. The design method of the unmanned aerial vehicle gallium arsenide solar cell array is easy to realize in engineering.
Drawings
The accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
Fig. 1 is a schematic diagram of a standard component in a gallium arsenide solar cell array design method for a solar unmanned aerial vehicle according to an embodiment of the present invention;
fig. 2 is a schematic diagram of a cell array in the gallium arsenide solar cell array design method for the solar unmanned aerial vehicle according to the embodiment of the invention.
In fig. 1, a label 1 is an anti-reverse diode, a label 2 is an output anode of the assembly, a label 3 is a gallium arsenide solar cell monomer, a label 4 is an edge of the assembly in a parallel direction, a label 5 is an output cathode of the assembly, and a label 6 is an edge of the assembly in a serial direction; in fig. 2, reference numeral 7 is an output anode of the gallium arsenide solar cell array, reference numeral 8 is an output cathode of the gallium arsenide solar cell array, and reference numeral 9 is a non-standard component in the gallium arsenide solar cell array.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
As shown in fig. 1-2, the invention provides a method for designing a solar unmanned aerial vehicle crystalline silicon solar cell array, which mainly comprises the following steps:
selecting a gallium arsenide battery monomer, namely selecting the gallium arsenide battery monomer according to the size of the wing, the conversion efficiency and the cost requirement, and determining the size, the maximum power point voltage and the maximum power of the gallium arsenide battery monomer;
designing a gallium arsenide battery assembly, namely determining the serial number of gallium arsenide battery monomers according to the input and output voltage requirement of an MPPT controller; determining the specifications of a standard gallium arsenide battery component and a non-standard gallium arsenide battery component; determining the gaps between monomers in the gallium arsenide cell component in the serial direction and the parallel direction according to the effective power generation area and the production process requirement; the positive electrode output of each battery in the gallium arsenide battery component is connected with an anti-reverse diode in series; the positive electrode and the negative electrode output in each serial direction in the assembly are connected in parallel through a confluence welding strip to form a positive electrode and a negative electrode of the assembly;
testing and grading the gallium arsenide battery assembly, namely testing a current-voltage curve of the assembly in a standard environment, and grading according to the maximum power point working voltage value of the assembly;
a gallium arsenide cell power generation array dividing step, namely extracting wing profiles, and determining the number of components in the power generation array along the chord length direction according to the curve length of the wing surfaces on the wings; determining the number of components along the wingspan direction according to the MPPT controller power corresponding to the power generation array; according to the grading result, the maximum power point working voltage value of the gallium arsenide battery pack in the same power generation array is required to be in the same grade;
and (3) gallium arsenide power generation array confluence design, wherein all gallium arsenide battery assemblies in the same power generation array are connected in parallel through confluence welding strips, and the positive and negative electrodes of the power generation array are led out and connected into corresponding MPPT controllers.
In the embodiment, the MPPT controller outputs 30V-60V of voltage, inputs 30V-60V of voltage and has the maximum power of 200W. The wing is a rectangular wing, the chord length is 620mm, and the length of the upper curve of the wing is 660 mm.
First, in this embodiment, a gaas cell with a conversion efficiency of 30% and a size of 20.5mm × 40.1mm is selected. The maximum power point voltage of the single body is 2.5V, and the maximum power is 0.25W.
According to the input and output voltage requirements of the MPPT controller, the gallium arsenide battery cells adopt a 16-string form.
According to the wing size and the component manufacturing process requirement and the like in the embodiment, 16 strings 6 are determined and are standard components in the embodiment, and the rest components are non-standard gallium arsenide battery components.
In the gallium arsenide battery component, the monomer series connection direction adopts a lamination design, the interval is 0mm, and the gap in the parallel connection direction is 0.7 mm.
In the gallium arsenide battery component, the anode output of each battery string is connected with an anti-reverse diode in series, and the thickness of the diode is 1.2 mm. The output positive electrode and the output negative electrode in each serial direction in the assembly are connected in parallel through the confluence welding strip to form the positive electrode and the negative electrode of the assembly.
The monomer of series direction is 8mm apart from the marginal width of subassembly in this embodiment subassembly, and the monomer of parallelly connected direction is 3mm apart from the marginal width of subassembly.
According to the length of the airfoil curve on the airfoil, the method determines that the components in the power generation array along the chord length direction are 2 standard components 16 in series and 6 in parallel and a non-standard component 16 in series and 3 in parallel, and the mode can realize the maximum gallium arsenide effective power generation area. In this embodiment the components are 20mm from the leading edge and 15mm from the trailing edge.
According to the maximum power 200W requirement of the MPPT controller in the embodiment, the number of the components of the power generation array in the wingspan direction is determined to be 3 groups, and the total number of the components is 9, namely 6 standard components and 6 non-standard components. The distance between the components is 1 mm.
And carrying out current-voltage curve test on the manufactured assembly in a standard environment, and grading according to the maximum power point working voltage value of the assembly, wherein the grading voltage intervals are 38V +/-0.5V, 39V +/-0.5V, 40V +/-0.5V, 41V +/-0.5V and 42V +/-0.5V.
And according to the grading result, arranging the gallium arsenide battery components in the same voltage interval in a power generation array.
All gallium arsenide battery assemblies in the power generation array are connected in parallel through the confluence welding strip, and the anode and the cathode of the power generation array are led out and connected into the corresponding MPPT controllers.
Through the technical scheme, the problem that the gallium arsenide battery cell is applied to the unmanned aerial vehicle due to high voltage and small size is solved. By the optimized design of the size of the component, the effective power generation area of the gallium arsenide battery on the unmanned aerial vehicle can be maximized; through the design that each string of batteries in the assembly is output with a positive series anti-reverse diode, the short-circuit fault of a single string of batteries can be effectively isolated; the assembly is segmented by the maximum power point voltage, the maximum power output of the gallium arsenide solar cell array can be realized, and the phenomenon of assembly matching failure is avoided. The design method of the unmanned aerial vehicle gallium arsenide solar cell array is easy to realize in engineering.
The above embodiments are only for explaining and explaining the technical solution of the present invention, but should not be construed as limiting the scope of the claims. It should be clear to those skilled in the art that any simple modification or replacement based on the technical solution of the present invention may be adopted to obtain a new technical solution, which falls within the scope of the present invention.
Claims (4)
1. A gallium arsenide solar cell array design method for a solar unmanned aerial vehicle is characterized by comprising the following steps:
selecting a gallium arsenide battery monomer, namely selecting the gallium arsenide battery monomer according to the size of the wing, the conversion efficiency and the cost requirement, and determining the size, the maximum power point voltage and the maximum power of the gallium arsenide battery monomer;
designing a gallium arsenide battery assembly, namely determining the serial number of gallium arsenide battery monomers according to the input and output voltage requirement of an MPPT controller; determining the specifications of a standard gallium arsenide battery component and a non-standard gallium arsenide battery component; determining the gaps between monomers in the gallium arsenide cell component in the serial direction and the parallel direction according to the effective power generation area and the production process requirement; the positive electrode output of each battery in the gallium arsenide battery component is connected with an anti-reverse diode in series; the positive electrode and the negative electrode output in each serial direction in the assembly are connected in parallel through a confluence welding strip to form a positive electrode and a negative electrode of the assembly;
testing and grading the gallium arsenide battery assembly, namely testing a current-voltage curve of the assembly in a standard environment, and grading according to the maximum power point working voltage value of the assembly;
a gallium arsenide cell power generation array dividing step, namely extracting wing profiles, and determining the number of components in the power generation array along the chord length direction according to the curve length of the wing surfaces on the wings; determining the number of components along the wingspan direction according to the MPPT controller power corresponding to the power generation array; according to the grading result, the maximum power point working voltage value of the gallium arsenide battery pack in the same power generation array is required to be in the same grade;
and (3) gallium arsenide power generation array confluence design, wherein all gallium arsenide battery assemblies in the same power generation array are connected in parallel through confluence welding strips, and the positive and negative electrodes of the power generation array are led out and connected into corresponding MPPT controllers.
2. The design method of the gallium arsenide solar cell array of the solar unmanned aerial vehicle as claimed in claim 1, wherein in the step of designing the gallium arsenide cell module, the gap required in the serial direction is controlled between 0mm and 1 mm; the parallel connection direction requires the gap to be controlled between 0.5mm and 1 mm; the thickness of the diode is not more than 1.2 mm; the width of the blank in the serial direction in the module is not more than 8mm, and the width of the blank in the parallel direction is not more than 3 mm.
3. The method of claim 1, wherein in GaAs cell module testing and grading, the voltage step interval is 1V.
4. The design method of the gallium arsenide solar cell array of the solar unmanned aerial vehicle as claimed in claim 1, wherein in the division of the gallium arsenide cell power generation array, the distance between the module and the front edge of the wing profile is 20 mm-50 mm, and the distance between the module and the back edge of the wing profile is 10 mm-30 mm; the distance between the components is 1 mm.
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20170331323A1 (en) * | 2016-05-13 | 2017-11-16 | Aurora Flight Sciences Corporation | Solar Power System and Method Thereof |
| CN107745819A (en) * | 2017-09-27 | 2018-03-02 | 重庆科创职业学院 | A kind of fixed-wing solar powered aircraft |
| CN109660200A (en) * | 2017-10-11 | 2019-04-19 | 海鹰航空通用装备有限责任公司 | Solar energy unmanned plane energy management system and solar energy unmanned plane with it |
| US20190172955A1 (en) * | 2017-12-05 | 2019-06-06 | Solaero Technologies Corp. | Laminar airfoil and the assembly and mounting of solar cell arrays on such airfoils |
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- 2020-09-24 CN CN202011016601.3A patent/CN114257172B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20170331323A1 (en) * | 2016-05-13 | 2017-11-16 | Aurora Flight Sciences Corporation | Solar Power System and Method Thereof |
| CN107745819A (en) * | 2017-09-27 | 2018-03-02 | 重庆科创职业学院 | A kind of fixed-wing solar powered aircraft |
| CN109660200A (en) * | 2017-10-11 | 2019-04-19 | 海鹰航空通用装备有限责任公司 | Solar energy unmanned plane energy management system and solar energy unmanned plane with it |
| US20190172955A1 (en) * | 2017-12-05 | 2019-06-06 | Solaero Technologies Corp. | Laminar airfoil and the assembly and mounting of solar cell arrays on such airfoils |
Non-Patent Citations (1)
| Title |
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| 王寅;呼文韬;: "太阳能飞机太阳电池组阵设计方法研究", 电源技术, no. 07 * |
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