CN114257172B - 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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- CN114257172B CN114257172B CN202011016601.3A CN202011016601A CN114257172B CN 114257172 B CN114257172 B CN 114257172B CN 202011016601 A CN202011016601 A CN 202011016601A CN 114257172 B CN114257172 B CN 114257172B
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- 229910001218 Gallium arsenide Inorganic materials 0.000 title claims abstract description 86
- JBRZTFJDHDCESZ-UHFFFAOYSA-N AsGa Chemical compound [As]#[Ga] JBRZTFJDHDCESZ-UHFFFAOYSA-N 0.000 title claims abstract description 85
- 238000013461 design Methods 0.000 title claims abstract description 34
- 238000000034 method Methods 0.000 title claims abstract description 19
- 238000010248 power generation Methods 0.000 claims abstract description 38
- 238000012360 testing method Methods 0.000 claims abstract description 10
- 239000000178 monomer Substances 0.000 claims abstract description 7
- 238000003466 welding Methods 0.000 claims description 8
- 238000006243 chemical reaction Methods 0.000 claims description 5
- 238000004519 manufacturing process Methods 0.000 claims description 4
- 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
- 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
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
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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
-
- 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
-
- 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
-
- 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
-
- 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
-
- 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
Abstract
The invention relates to the technical field of solar unmanned aerial vehicles and discloses a gallium arsenide solar cell array design method of a solar unmanned aerial vehicle. The operation steps comprise: gallium arsenide battery monomer selection, component design, component test, grading, power generation array division and power generation pool array converging design. Through the optimal design of the component size, the maximization of the effective power generation area of the gallium arsenide battery on the unmanned aerial vehicle can be realized; through the design of the forward-series anti-reverse diode output of each string of batteries in the assembly, the short-circuit fault of a single string of batteries can be effectively isolated; the maximum power point voltage is used for segmenting the components, so that the maximum power output of the gallium arsenide solar cell array can be realized, and the component matching failure phenomenon is avoided. The unmanned aerial vehicle gallium arsenide solar cell array design method 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 of 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 and low in cost, and has wide application prospect. The system can be used for civil air research, weather forecast, environment and disaster monitoring, crop telemetering, traffic control, telecommunication and television service, natural protection area monitoring and the like; the method can be used for border patrol, reconnaissance, communication relay and the like in military.
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 wing airfoil curved surface application and the like. At present, according to different application modes of solar cell modules, solar unmanned aerial vehicles are mainly divided into skin integrated unmanned aerial vehicles and monocoque unmanned aerial vehicles, and the two unmanned aerial vehicles have advantages and disadvantages. After the solar cell modules are laid on the machine, a plurality of solar cell arrays are required to be formed through series-parallel connection among the modules. The power generation power and voltage range of the solar cell array need to be matched with corresponding MPPT (maximum power point tracking) controllers. The design of the solar cell array is important, and the design of the solar cell array is related to whether the solar cell can realize the maximum power output and the full energy collection efficiency. The design of the solar cell array on the unmanned aerial vehicle needs to consider the influences of wing-shaped curved surfaces, flight attitudes and the like. Currently, a solar unmanned aerial vehicle in the near space at home and abroad is mainly carried with a monocrystalline silicon battery assembly to carry out low-altitude flight verification. With the increase of demands of flying height, flying endurance and the like, the application of the gallium arsenide battery assembly is one of the future development trends.
The design method and the reference experience of the gallium arsenide solar cell array of the solar unmanned aerial vehicle are less at present through verification. Therefore, the invention provides a design method of a gallium arsenide solar cell array of a solar unmanned aerial vehicle.
Disclosure of Invention
The invention provides a design method of a gallium arsenide solar cell array of a solar unmanned aerial vehicle, which effectively isolates short-circuit faults of single-string cells, realizes maximum power output and full energy collection efficiency and is easy to realize in engineering.
The invention discloses a design method of a gallium arsenide solar cell array of a solar unmanned aerial vehicle, which comprises the following steps:
a gallium arsenide battery cell type selection step, namely selecting the gallium arsenide battery cell type according to the wing size, conversion efficiency and cost requirements, and determining the size, the maximum power point voltage and the maximum power of the gallium arsenide battery cell;
the gallium arsenide battery pack design step, according to the MPPT controller input/output voltage requirement, determining the serial number of gallium arsenide battery cells; determining standard gallium arsenide battery components and non-standard gallium arsenide battery component specifications; according to the effective power generation area and the production process requirements, determining gaps between monomers in the serial direction and the parallel direction in the gallium arsenide battery assembly; the positive electrode of each battery in the gallium arsenide battery assembly outputs a serial anti-reflection diode; the positive electrode and the negative electrode of each serial direction output in the assembly are connected in parallel through a current collecting welding strip to form the positive electrode and the 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 the assembly according to the maximum power point working voltage value of the assembly;
dividing a gallium arsenide battery power generation array, 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 upper wing surface of the wing; determining the number of components along the span 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 assembly in the same power generation array is required to be in the same grade;
and the gallium arsenide power generation array confluence design step is that all gallium arsenide battery components in the same power generation array are connected in parallel through a confluence welding strip, and simultaneously, the anode and the cathode of the power generation array are led out and connected into a corresponding MPPT controller.
Further, in the gallium arsenide battery pack design step, the gap is required to be controlled between 0mm and 1mm in the serial direction; the parallel direction requires the gap to be controlled between 0.5mm and 1 mm; the thickness of the diode is not more than 1.2mm; the margin width of the components in the serial direction is not more than 8mm, and the margin width of the components in the parallel direction is not more than 3mm.
Further, in gallium arsenide battery pack testing and grading, the grading voltage interval is 1V.
Further, in the division of the gallium arsenide battery power generation array, the distance between the components and the wing profile front edge is 20-50 mm, and the distance between the components and the wing profile rear edge is 10-30 mm; the spacing between the modules is 1mm.
The invention solves the problem of application of gallium arsenide battery monomer on unmanned aerial vehicle due to high voltage and small size. Through the optimal design of the component size, the maximization of the effective power generation area of the gallium arsenide battery on the unmanned aerial vehicle can be realized; through the design of the forward-series anti-reverse diode output of each string of batteries in the assembly, the short-circuit fault of a single string of batteries can be effectively isolated; the maximum power point voltage is used for segmenting the components, so that the maximum power output of the gallium arsenide solar cell array can be realized, and the component matching failure phenomenon is avoided. The unmanned aerial vehicle gallium arsenide solar cell array design method is easy to realize in engineering.
Drawings
The accompanying drawings, which are included to provide a further understanding of 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 evident that the drawings in the following description are only some embodiments of the present invention and that other drawings may be obtained from these drawings without inventive effort for a person of ordinary skill in the art.
Fig. 1 is a schematic diagram of a standard component in a design method of a gallium arsenide solar cell array of a solar unmanned aerial vehicle according to an embodiment of the invention;
fig. 2 is a schematic diagram of a cell array in a gallium arsenide solar cell array design method of a solar unmanned aerial vehicle according to an embodiment of the invention.
In fig. 1, reference numeral 1 is an anti-reflection diode, reference numeral 2 is a component output positive electrode, reference numeral 3 is a gallium arsenide solar cell, reference numeral 4 is a component parallel direction edge, reference numeral 5 is a component output negative electrode, and reference numeral 6 is a component series direction edge; in fig. 2, reference numeral 7 denotes a positive output electrode of the gallium arsenide solar cell array, reference numeral 8 denotes a negative output electrode of the gallium arsenide solar cell array, and reference numeral 9 denotes a nonstandard component in the gallium arsenide solar cell array.
Detailed Description
The invention is described in further detail below with reference to the accompanying drawings.
As shown in fig. 1-2, the invention provides a design method of a solar unmanned aerial vehicle crystalline silicon solar cell array, which mainly comprises the following steps:
a gallium arsenide battery cell type selection step, namely selecting the gallium arsenide battery cell type according to the wing size, conversion efficiency and cost requirements, and determining the size, the maximum power point voltage and the maximum power of the gallium arsenide battery cell;
the gallium arsenide battery pack design step, according to the MPPT controller input/output voltage requirement, determining the serial number of gallium arsenide battery cells; determining standard gallium arsenide battery components and non-standard gallium arsenide battery component specifications; according to the effective power generation area and the production process requirements, determining gaps between monomers in the serial direction and the parallel direction in the gallium arsenide battery assembly; the positive electrode of each battery in the gallium arsenide battery assembly outputs a serial anti-reflection diode; the positive electrode and the negative electrode of each serial direction output in the assembly are connected in parallel through a current collecting welding strip to form the positive electrode and the 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 the assembly according to the maximum power point working voltage value of the assembly;
dividing a gallium arsenide battery power generation array, 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 upper wing surface of the wing; determining the number of components along the span 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 assembly in the same power generation array is required to be in the same grade;
and the gallium arsenide power generation array confluence design step is that all gallium arsenide battery components in the same power generation array are connected in parallel through a confluence welding strip, and simultaneously, the anode and the cathode of the power generation array are led out and connected into a corresponding MPPT controller.
In the embodiment, the output voltage of the MPPT controller is 30V-60V, the input voltage is 30V-60V, and the maximum power of the MPPT controller is 200W. The wing is a rectangular wing, the chord length is 620mm, and the curve length on the wing profile is 660mm.
Firstly, in this embodiment, gallium arsenide battery cells with conversion efficiency of 30% and size of 20.5mm by 40.1mm are selected. The maximum power point voltage of the monomer 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 cell adopts a 16-string form.
According to the wing size, the component manufacturing process requirements and the like in the embodiment, the 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 assembly of the embodiment, the single bodies are in a stacked design in the serial direction, the interval is 0mm, and the gap in the parallel direction is 0.7mm.
In the gallium arsenide battery assembly of the embodiment, each string of battery positive electrode outputs a serial anti-reflection diode, and the thickness of the diode is 1.2mm. And outputting an anode and a cathode in each serial direction in the assembly, and connecting the anode and the cathode in parallel through a current collecting welding strip to form the anode and the cathode of the assembly.
In the embodiment, the width of the single bodies in the serial direction from the edge of the assembly is 8mm, and the width of the single bodies in the parallel direction from the edge of the assembly is 3mm.
According to the curve length of the airfoil surface on the airfoil, the embodiment determines that the components in the chord length direction in the power generation array are 2 standard components with 16 strings and 6 parallel strings and one nonstandard component with 16 strings and 3 parallel strings, and the mode can achieve the maximum gallium arsenide effective power generation area. The assembly in this embodiment is 20mm from the leading edge of the wing and 15mm from the trailing edge of the wing.
According to the maximum power 200W requirement of the MPPT controller in the present embodiment, the number of components of the power generation array in the spanwise direction is determined to be 3 groups, and 9 components are 6 standard components and 6 nonstandard components respectively. The spacing between the modules is 1mm.
And (3) testing a current-voltage curve of 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 interval is 38 V+/-0.5V, 39 V+/-0.5V, 40 V+/-0.5V, 41 V+/-0.5V and 42 V+/-0.5V.
And according to the grading result, the gallium arsenide battery assembly in the same voltage interval is arranged in a power generation array.
All gallium arsenide battery components in the power generation array are connected in parallel through a current collecting welding strip, and meanwhile, the anode and the cathode of the power generation array are led out and connected into a corresponding MPPT controller.
Through the technical scheme, the problem that the gallium arsenide battery monomer is applied to the unmanned aerial vehicle due to high voltage and small size is solved. Through the optimal design of the component size, the maximization of the effective power generation area of the gallium arsenide battery on the unmanned aerial vehicle can be realized; through the design of the forward-series anti-reverse diode output of each string of batteries in the assembly, the short-circuit fault of a single string of batteries can be effectively isolated; the maximum power point voltage is used for segmenting the components, so that the maximum power output of the gallium arsenide solar cell array can be realized, and the component matching failure phenomenon is avoided. The unmanned aerial vehicle gallium arsenide solar cell array design method is easy to realize in engineering.
The above embodiments are only limited to the explanation and description of the technical solutions 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 substitution of the technical solution of the present invention results in a new technical solution that falls within the scope of the present invention.
Claims (4)
1. The design method of the gallium arsenide solar cell array of the solar unmanned aerial vehicle is characterized by comprising the following steps of:
a gallium arsenide battery cell type selection step, namely selecting the gallium arsenide battery cell type according to the wing size, conversion efficiency and cost requirements, and determining the size, the maximum power point voltage and the maximum power of the gallium arsenide battery cell;
the gallium arsenide battery pack design step, according to the MPPT controller input/output voltage requirement, determining the serial number of gallium arsenide battery cells; determining standard gallium arsenide battery components and non-standard gallium arsenide battery component specifications; according to the effective power generation area and the production process requirements, determining gaps between monomers in the serial direction and the parallel direction in the gallium arsenide battery assembly; the positive electrode of each battery in the gallium arsenide battery assembly outputs a serial anti-reflection diode; the positive electrode and the negative electrode of each serial direction output in the assembly are connected in parallel through a current collecting welding strip to form the positive electrode and the 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 the assembly according to the maximum power point working voltage value of the assembly;
dividing a gallium arsenide battery power generation array, 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 upper wing surface of the wing; determining the number of components along the span 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 assembly in the same power generation array is required to be in the same grade;
and the gallium arsenide power generation array confluence design step is that all gallium arsenide battery components in the same power generation array are connected in parallel through a confluence welding strip, and simultaneously, the anode and the cathode of the power generation array are led out and connected into a corresponding MPPT controller.
2. The method for designing a gallium arsenide solar cell array of a solar unmanned aerial vehicle according to claim 1, wherein in the step of designing the gallium arsenide cell assembly, the gap is controlled between 0mm and 1mm in the serial direction; the parallel direction requires the gap to be controlled between 0.5mm and 1 mm; the thickness of the diode is not more than 1.2mm; the margin width of the components in the serial direction is not more than 8mm, and the margin width of the components in the parallel direction is not more than 3mm.
3. The method of claim 1, wherein in the testing and grading of the gallium arsenide battery assembly, the voltage interval between the steps is 1V.
4. The method for designing the gallium arsenide solar cell array of the solar unmanned aerial vehicle according to claim 1, wherein in the division of the gallium arsenide solar cell power generation array, the distance between a component and the front edge of an airfoil is 20-50 mm, and the distance between the component and the rear edge of the airfoil is 10-30 mm; the spacing between the modules is 1mm.
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
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| WO2017197245A1 (en) * | 2016-05-13 | 2017-11-16 | Aurora Flight Sciences Corporation | Solar power system and method thereof |
| EP3496163B1 (en) * | 2017-12-05 | 2020-09-23 | SolAero Technologies Corp. | Methods of fabricating solar cell arrays, vehicles and airfoils incorporating solar cells |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
Non-Patent Citations (1)
| Title |
|---|
| 太阳能飞机太阳电池组阵设计方法研究;王寅;呼文韬;;电源技术(第07期);全文 * |
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