WO2020096290A1 - Panneau de cellules solaires de satellite artificiel - Google Patents

Panneau de cellules solaires de satellite artificiel Download PDF

Info

Publication number
WO2020096290A1
WO2020096290A1 PCT/KR2019/014772 KR2019014772W WO2020096290A1 WO 2020096290 A1 WO2020096290 A1 WO 2020096290A1 KR 2019014772 W KR2019014772 W KR 2019014772W WO 2020096290 A1 WO2020096290 A1 WO 2020096290A1
Authority
WO
WIPO (PCT)
Prior art keywords
bar
busing
satellite
solar
solar cell
Prior art date
Application number
PCT/KR2019/014772
Other languages
English (en)
Korean (ko)
Inventor
김정식
안기태
장지영
전진형
Original Assignee
엘지전자 주식회사
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by 엘지전자 주식회사 filed Critical 엘지전자 주식회사
Publication of WO2020096290A1 publication Critical patent/WO2020096290A1/fr

Links

Images

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
    • H01L31/02—Details
    • H01L31/02002—Arrangements for conducting electric current to or from the device in operations
    • H01L31/02005—Arrangements for conducting electric current to or from the device in operations for device characterised by at least one potential jump barrier or surface barrier
    • H01L31/02008—Arrangements for conducting electric current to or from the device in operations for device characterised by at least one potential jump barrier or surface barrier for solar cells or solar cell modules
    • H01L31/0201—Arrangements for conducting electric current to or from the device in operations for device characterised by at least one potential jump barrier or surface barrier for solar cells or solar cell modules comprising specially adapted module bus-bar structures
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/42—Arrangements or adaptations of power supply systems
    • B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/42—Arrangements or adaptations of power supply systems
    • B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
    • B64G1/443—Photovoltaic cell arrays
    • 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
    • H01L31/02—Details
    • 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
    • H01L31/02—Details
    • H01L31/0224—Electrodes
    • 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
    • H01L31/02—Details
    • H01L31/0224—Electrodes
    • H01L31/022408—Electrodes for devices characterised by at least one potential jump barrier or surface barrier
    • H01L31/022425—Electrodes for devices characterised by at least one potential jump barrier or surface barrier for 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
    • H01L31/05—Electrical interconnection means between PV cells inside the PV module, e.g. series connection of PV 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
    • H01L31/05—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
    • H01L31/0508—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 the interconnection means having a particular shape
    • 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
    • H01L31/052—Cooling means directly associated or integrated with the PV cell, e.g. integrated Peltier elements for active cooling or heat sinks directly associated with the PV cells
    • 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
    • H02S10/00—PV power plants; Combinations of PV energy systems with other systems for the generation of electric power
    • H02S10/40—Mobile PV generator systems
    • 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

Definitions

  • the present invention relates to a solar panel for satellites, and is a study conducted with the support of the Korea Research Foundation-Cosmic Core Technology Development Project (NRF-2017M1A3A3A03016626), funded by the government (Ministry of Science and ICT) in 2018.
  • NEF-2017M1A3A3A03016626 Korea Research Foundation-Cosmic Core Technology Development Project
  • Such solar cells are widely used as devices for supplying power to satellites that perform specific tasks in extreme environments.
  • a solar cell module for a satellite to which a plurality of solar cells is applied is operated by being exposed to an extreme environment, safety and reliability of a solar cell module that can withstand extreme environments rather than manufacturing costs are becoming more important.
  • the solar cell module applied to an artificial satellite must withstand vibrations generated by a projectile generated when the satellite is mounted on a projectile and escapes the earth, and after reaching a certain orbit in outer space, the artificial satellite is applied to outer space. After exposure, it must withstand extreme temperatures.
  • the temperature change range in the rainwater space reaches at least 200 ° C.
  • thermal expansion and the resulting thermal expansion stress may be a problem in an extreme space environment where temperature change is very large.
  • An object of the present invention is to provide a solar panel for satellite with improved reliability. More specifically, the object of the present invention is to provide a solar panel for satellites that can minimize the disconnection between the busing bar and the interconnector by minimizing the thermal expansion rate and the thermal expansion stress of the busing bar.
  • a plurality of cell strings in which a plurality of satellite solar cells provided in each are connected in series in a first direction by an interconnector and spaced apart from each other in a second direction crossing the first direction ; And disposed at the ends of each of the plurality of cell strings, elongated in a second direction, and electrically connected to an interconnector connected to the last solar cell of each of the plurality of cell strings, wherein the plurality of cell strings are electrically connected to each other, It includes; a busing bar connected to the junction box, the busing bar includes a connection portion that connects each other between a plurality of contact point portions and a plurality of contact points to which an interconnector is connected, the width of the first direction of the connecting portion of the busing bar is The contact point portion is narrower than the width in the first direction, and the connecting portion of the bussing bar has a first long hole extending in the second direction.
  • each of the plurality of solar cells for satellites is a semiconductor substrate on which a pn junction is formed, a first electrode on the front surface of the semiconductor substrate, a second electrode on the back surface of the semiconductor substrate, and a cover glass having the same area as the semiconductor substrate on the front surface of the semiconductor substrate. Is attached, the cover glass is attached to the front surface of each semiconductor substrate provided in each solar cell, and is spaced apart from each other between each semiconductor substrate.
  • the interconnector is connected to the first electrode between the cover glass of each solar cell and the semiconductor substrate, and is connected to the second electrode provided on the rear surface of the adjacent solar cell in the first direction, and each solar cell is in the first direction
  • the length of the second direction may be longer than the length of.
  • the length of the second direction of the busing bar may be greater than the length of the second direction of each solar cell or 1.5 times or more the length of the second direction of each solar cell.
  • the length of the second direction of the busing bar may be the same as or longer than the length between both ends of the second direction of the cell strings of the plurality of cell strings.
  • the busing bar may include a second long hole extending in a second direction in the contact point portion.
  • the second long hole provided in the contact point portion of the busing bar may be provided in a plurality of spaced apart in the first direction.
  • center positions of the plurality of second long holes spaced apart in the first direction may be alternately positioned in the second direction.
  • the length of the first long hole may be longer than the length of the second long hole.
  • the solar cell panel for a satellite includes a solar cell array substrate that adheres to the rear surface of a plurality of cell strings to support a plurality of solar cells and emit radiant heat emitted from the sun.
  • the and connecting portion may be adhered to the solar cell array substrate.
  • the bussing bar has a connection portion having a relatively smaller width than the contact point portion, and a first long hole in the connection portion to minimize the thermal expansion rate and thermal expansion stress of the busing bar, thereby The disconnection between the bar and the interconnector can be prevented.
  • FIG. 1 schematically shows an artificial satellite 1 to which a solar panel 10 for an artificial satellite is applied according to an example of the present invention.
  • FIG. 2 is a perspective view of the solar panel 10 for satellites provided in the wing portion of the satellite 1 in FIG. 1.
  • FIG. 3 is an enlarged view of a portion K1 in FIG. 2.
  • FIG. 4 and 5 are diagrams for explaining the structure of the solar cell 200 for the satellite shown in FIG.
  • FIG. 6 is a view for explaining the structure of a cell string of a solar panel according to the present invention and a bussing bar connected to each cell string.
  • FIG. 7 is an enlarged view of upper portions of the first and second strings in FIG. 6A in order to more specifically describe the busing bar according to an example of the present invention.
  • FIG. 8 is a cross-sectional view when the solar panel shown in FIG. 7 is viewed from above in the second direction.
  • FIG. 9 is a view for explaining the form in which the conventional busing bar is adhered to the solar cell array substrate with the present invention.
  • the thickness is enlarged to clearly express the various layers and regions.
  • a portion of a layer, film, region, plate, or the like is said to be “above” another portion, this includes not only the case “directly above” other portions, but also other portions in between.
  • one part is “just above” another part, it means that there is no other part in the middle.
  • a part is formed “overall” on another part, it means that not only is formed on the entire surface (or front side) of the other part, but also not formed on a part of the edge.
  • the meaning that the thickness, width, or length of a component is the same is compared with the thickness, width, or length of a second component, in which the thickness, width, or length of a first component is considered in consideration of process errors. Therefore, it means that it is in the error range of 10%.
  • FIG. 1 is a simplified illustration of an artificial satellite 1 to which a solar panel 10 for an artificial satellite is applied according to an example of the present invention
  • FIG. 2 is for an artificial satellite provided in a wing portion of the artificial satellite 1 in FIG. 1.
  • 3 is a perspective view of the solar panel 10, and FIG. 3 is an enlarged view of a portion K1 in FIG.
  • the solar panel 10 for an artificial satellite can be applied by being located at a wing portion of the satellite 1 to supply power available to the satellite 1. .
  • the plurality of solar cells 200 included in each of the plurality of cell strings may be applied to a satellite solar cell 200 applicable to an extreme space environment in which a temperature change of at least 200 ° C due to radiant heat of solar light is applied. .
  • the solar cell 200 for satellites has a metal material having an extremely low thermal expansion coefficient, an electrode material, an interconnector 260 material, and a lead wire of each solar cell 200. It can be used as a material.
  • the glass substrate may not cover the plurality of solar cells 200 and the interconnector 260 (not shown) in common.
  • the interconnector 260 may be exposed to outer space without being covered by the glass substrate.
  • each solar cell 200 includes a cover glass (not shown), a front electrode (not shown), a semiconductor layer (not shown) and a back electrode (not shown) for photoelectric conversion, and each front electrode includes The interconnector 260 (not shown) may be electrically connected.
  • each of the interconnectors 260 may connect a plurality of solar cells 200 in series in a first horizontal direction (x) or a second horizontal direction (y).
  • a plurality of satellite solar cells 200 may be spaced apart in a first horizontal direction (x) and a second horizontal direction (y).
  • the solar cell array substrate 100 supports a plurality of solar cells 200 and emits radiant heat emitted from the sun.
  • the rear surfaces of the plurality of cell strings may be adhered to the front surface of the solar cell array substrate to support the plurality of cell strings.
  • the rear surfaces of the plurality of solar cells 200 included in the plurality of cell strings are adhered to the front surface of the solar cell array substrate 100 through the cell adhesive 400, as shown in FIG. 3. Can be.
  • FIG. 4 and 5 are diagrams for explaining the structure of the solar cell 200 for the satellite shown in FIG.
  • FIG. 4 is a perspective view for explaining the structure of the solar cell 200 for satellite shown in FIG. 3
  • FIG. 5 is a first direction (x) for explaining the structure of the solar cell 200 for satellite shown in FIG. ) It is a cross-sectional view.
  • the solar cell 200 for satellite includes a semiconductor substrate 240, a front electrode 230, a rear electrode 250, a cover glass 210, and an interconnector 260. can do.
  • the semiconductor substrate 240 may form a pn junction therein to generate solar light incident from the outside, and as shown in FIG. 4 on the front surface of the semiconductor substrate 240, a first horizontal direction
  • the front electrode 230 may be formed including a plurality of finger electrodes extended in (x) and a busbar electrode extending in the second direction (y) to connect the plurality of finger electrodes to each other.
  • the rear electrode 250 may be entirely formed on the rear surface of the semiconductor substrate 240.
  • one end of the interconnector 260 is electrically connected to the busbar electrode of the front electrode 230 and the other end is elongated in the first horizontal direction (x), as shown in FIG. 5. Can be withdrawn outside.
  • the cover glass 210 may be adhered to the front surface of the semiconductor substrate 240 on which the front electrode 230 is formed using a cover glass adhesive 220 such as transparent epoxy.
  • the area of the cover glass 210 may be formed by bonding the cover glass adhesive 220 to the front surface of the semiconductor substrate 240 in the same area and shape as the semiconductor substrate 240. have.
  • the difference between the area of the cover glass 210 and the area of the semiconductor substrate 240 may be within 10%.
  • each of the satellite solar cells 200 is one of electrodes having different polarities provided in the plurality of satellite solar cells 200.
  • Interconnector 260 is provided to be connected to an electrode having polarity (eg, front electrode), and a cover glass 210 may be attached to the front surface of each of the plurality of satellite solar cells 200. .
  • the cover glass 210 attached to the battery 200 and the cover glass 210 attached to the second solar cell 200 may be spaced apart from each other between the first and second solar cells 200.
  • each solar cell 200 may have a longer length (Ly) in the second direction (y) than a length (Lx) in the first direction (x).
  • the first direction length Lx of the solar cell 200 is relatively thinned, so that when the cell strings have the same length, more solar cells 200 are provided in each cell string, thereby outputting the solar panel.
  • the voltage can be further increased.
  • each cell string formed of the above-described satellite solar cell 200 and both ends of each cell string may be connected to the bussing bar.
  • FIG. 6 is a view for explaining the structure of a cell string of a solar panel according to the present invention and a bussing bar connected to each cell string
  • FIG. 6 (a) is a shape looking at the solar panel from above
  • FIG. (b) is an enlarged view of the portion K2 shown in (a) of FIG. 6
  • (c) of FIG. 6 is a view of the portion K2 shown in (a) of FIG. 6 from the side in the second direction (y). It shows the vertical cross section of the time.
  • FIG. 7 is an enlarged view of upper portions of the first and second strings in FIG. 6A in order to more specifically describe the busing bar according to an example of the present invention
  • FIG. 8 is a view illustrated in FIG. 7 The cross section is shown when the battery panel is viewed from above in the second direction (y).
  • FIG. 9 is a view for explaining the form in which the conventional busing bar is adhered to the solar cell array substrate with the present invention.
  • each of the plurality of cell strings (ST1 ⁇ STn) are located in the first direction (x) long, the first direction (x) and A plurality of cell strings ST1 to STn may be spaced apart from each other in the crossing second direction y.
  • each of the plurality of cell strings ST1 to STn may have a plurality of satellite solar cells 200 provided in each of them connected in series in the first direction x by the interconnector 260.
  • the busing bar 300 may be disposed to extend in the second direction (y) at the ends of each of the cell strings ST1 to STn.
  • the busing bar 300 is electrically connected to the interconnector 260 connected to the last solar cell 200 of each of the plurality of cell strings ST1 to STn, so that the plurality of cell strings ST1 to STn are electrically connected to each other. It may be connected to a junction box (not shown).
  • first cell string ST1 and the second cell string ST2 may be connected to each other in series by a busing bar 300 that is disposed to extend in the second direction y.
  • the second direction length L300 of the busing bar 300 is greater than the length Ly of the second direction of each solar cell 200 in FIGS. 6 and 7 or the length of the second direction of each solar cell 200 It may be 1.5 times or more of (Ly).
  • the length of the second direction L300 of the busing bar 300 may be equal to or longer than the length between both ends of the second direction y of the at least two cell strings among the plurality of cell strings ST1 to STn.
  • the length L300 of the second direction of the busing bar 300 is directly adjacent to each other, but between both ends of the second direction y of the two cell strings spaced apart in the second direction y.
  • the same case as the length (WTS) is shown as an example.
  • the busing bar 300 may include a plurality of contact point portions 310 and a connection portion 320 as illustrated in FIGS. 6 and 7.
  • the interconnector 260 connected to the last solar cell 200 of each cell string will be located on the front of the contact point portion 310 of the busing bar 300 Can be.
  • the front surface of the busing bar 300 refers to a surface in which light is incident from the solar panel for satellites, and the rear surface of the busing bar 300 is bonded to the solar cell array substrate. It means noodles.
  • the connecting portion 320 of the busing bar 300 is located between the contact point portions 310 as the rest of the busing bar 300 except for the contact point portion 310 to connect the plurality of contact point portions 310 to each other. have.
  • the contact point portion 310 and the connection portion 320 of the busing bar 300 have a first direction width W320 of the connection portion 320 of the busing bar 300. It is formed narrower than the first direction width W310 of the contact point portion 310 so that it can be easily distinguished visually.
  • FIGS. 6 and 7 are illustrated as an example in which the first direction width W310 of the contact point portion 310 is approximately twice that of the first direction width W320 of the connection part 320, but the contact point
  • the first direction width W310 of the portion 310 may be formed between 1.5 times to 2.5 times the first direction width W320 of the connection part 320.
  • the first direction width (W310) of the contact point portion 310 is made larger than the first direction width (W320) of the connection portion 320, thereby increasing the physical adhesion between the busing bar (300) and the interconnector (260).
  • the thermal expansion coefficient that expands and contracts in the second direction (y), which is the longitudinal direction of the busing bar 300 is relatively small by making the width (W320) of the first direction of the connection part (320) relatively small. While reducing, it is possible to relieve the thermal expansion stress of the busing bar (300).
  • a difference in thermal expansion in the second direction (y) of the busing bar 300 may occur due to an excessive temperature difference generated in space, thereby increasing the thermal expansion stress of the busing bar 300 and the busing bar 300 )
  • the number of thermal expansion and thermal contraction increases, physical bonding between the busing bar 300 and the interconnector 260 may drop, and the present invention can be reduced.
  • connection part 320 may include a first long hole H1 extending in the second direction (y).
  • a second long hole H2 extending in the second direction y may be provided at the contact point portion 310.
  • the thermal expansion stress may be reduced to further reduce the welding defect rate.
  • the second long hole H2 provided in the contact point portion 310 of the busing bar 300 may be spaced apart in the first direction x to be provided in plural.
  • the length LH2 of the plurality of second long holes H2 spaced apart in the first direction x may be the same or different from each other, and the length LH2 of the plurality of second long holes H2 spaced apart in the first direction x may be the same.
  • the central positions may be the same or may be located alternately in the second direction (y).
  • the length LH1 of the first long hole H1 may be formed to be longer than the length LH2 of the second long hole H2.
  • the busing bar 300 of the solar panel for satellite according to the present invention is provided with a first long hole H1 in the connection portion 320, thereby reducing the thermal expansion stress of the busing bar 300, thereby In a space environment, a phenomenon in which the busting bar 300 and the interconnector 260 are disconnected due to thermal expansion stress of the busing bar 300 may be minimized.
  • the contact point portion 310 and the connection portion 320 of the busing bar 300 may be adhered to the solar cell array substrate by the cell adhesive 400.
  • the thermal expansion rate of the busing bar 300 is further increased. By reducing, the thermal expansion stress of the busing bar 300 can be further reduced.
  • the busing bar 300 applied to the conventional solar panel for satellites adheres only the portion of the cell string connected to the interconnector 260 of the cell string to the solar cell array substrate with the cell adhesive 400. And between the cell string and the cell string, the busing bar 300 and the solar cell array substrate 100 had a structure spaced apart from each other.
  • the contact point portion 310 of the busing bar 300 as well as the connecting portion 320 are adhered to the solar cell array substrate, thereby thermal expansion of the busing bar 300 It is possible to further suppress the difference in rate, thereby reducing the thermal expansion stress of the busing bar 300.
  • the material of the busing bar 300 may be formed of an alloy containing iron (Fe), nickel (Ni), and cobalt (Co) as a main component. Can be.
  • iron (Fe) content may be mixed between 50% to 60% by weight, nickel (Ni) between 25% to 35% by weight, and cobalt (Co) between 15% to 20% by weight, ,
  • chromium (Cr) and the like may be further contained in a small amount.
  • the coefficient of thermal expansion of the busing bar 300 itself can be reduced to a level similar to that of glass or alumina.
  • the present invention can minimize the thermal expansion rate of the busing bar 300 in an extreme space environment where temperature changes are extremely severe, thereby preventing disconnection between the busing bar 300 and the interconnector 260.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Physics & Mathematics (AREA)
  • Physics & Mathematics (AREA)
  • Condensed Matter Physics & Semiconductors (AREA)
  • Electromagnetism (AREA)
  • Computer Hardware Design (AREA)
  • Microelectronics & Electronic Packaging (AREA)
  • Power Engineering (AREA)
  • Sustainable Development (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Energy (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Photovoltaic Devices (AREA)

Abstract

La présente invention concerne un panneau de cellules solaires de satellite artificiel. Un panneau de cellules solaires selon un mode de réalisation de la présente invention comprend : une pluralité de séries de cellules dans lesquelles une pluralité de cellules solaires de satellite artificiel disposées respectivement à l'intérieur de celles-ci sont connectées en série dans une première direction par un interconnecteur et qui sont espacées l'une de l'autre dans une seconde direction croisant la première direction ; et des barres de douille qui sont allongées dans la seconde direction aux extrémités de la pluralité de séries de cellules, et qui sont électriquement connectées à l'interconnecteur connecté à la dernière cellule solaire de chaque série de la pluralité de séries de cellules de telle sorte que les séries de la pluralité de séries de cellules sont électriquement connectées les unes aux autres ou sont connectées à une boîte de jonction, les barres de douille comprenant une pluralité de parties de point de contact auxquelles l'interconnecteur est connecté et de parties de connexion pour connecter mutuellement une pluralité de points de contact ; une première largeur directionnelle des parties de connexion des barres de douille étant plus étroite qu'une première largeur directionnelle des parties de point de contact ; et les parties de connexion des barres de douille comprenant des premiers trous allongés dans la seconde direction.
PCT/KR2019/014772 2018-11-05 2019-11-01 Panneau de cellules solaires de satellite artificiel WO2020096290A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
KR1020180134810A KR102589092B1 (ko) 2018-11-05 2018-11-05 인공 위성용 태양 전지 패널
KR10-2018-0134810 2018-11-05

Publications (1)

Publication Number Publication Date
WO2020096290A1 true WO2020096290A1 (fr) 2020-05-14

Family

ID=70610954

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/KR2019/014772 WO2020096290A1 (fr) 2018-11-05 2019-11-01 Panneau de cellules solaires de satellite artificiel

Country Status (2)

Country Link
KR (1) KR102589092B1 (fr)
WO (1) WO2020096290A1 (fr)

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20060085564A (ko) * 2005-01-24 2006-07-27 토야마 키카이 가부시키가이샤 리드 구조
US20080216887A1 (en) * 2006-12-22 2008-09-11 Advent Solar, Inc. Interconnect Technologies for Back Contact Solar Cells and Modules
US20090139557A1 (en) * 2007-11-30 2009-06-04 Douglas Rose Busbar connection configuration to accommodate for cell misalignment
US20120192915A1 (en) * 2009-10-07 2012-08-02 Pythagoras Solar Inc. Photovoltaic module and array and method of manufacture thereof
US20130062956A1 (en) * 2010-06-15 2013-03-14 Tenksolar, Inc. Cell-to-grid redundandt photovoltaic system

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2009043872A (ja) * 2007-08-08 2009-02-26 Sharp Corp 太陽電池モジュールおよびその製造方法

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20060085564A (ko) * 2005-01-24 2006-07-27 토야마 키카이 가부시키가이샤 리드 구조
US20080216887A1 (en) * 2006-12-22 2008-09-11 Advent Solar, Inc. Interconnect Technologies for Back Contact Solar Cells and Modules
US20090139557A1 (en) * 2007-11-30 2009-06-04 Douglas Rose Busbar connection configuration to accommodate for cell misalignment
US20120192915A1 (en) * 2009-10-07 2012-08-02 Pythagoras Solar Inc. Photovoltaic module and array and method of manufacture thereof
US20130062956A1 (en) * 2010-06-15 2013-03-14 Tenksolar, Inc. Cell-to-grid redundandt photovoltaic system

Also Published As

Publication number Publication date
KR102589092B1 (ko) 2023-10-16
KR20200051441A (ko) 2020-05-13

Similar Documents

Publication Publication Date Title
CN203277445U (zh) 太阳能电池模块
WO2011037373A2 (fr) Module photovoltaïque et son procédé de fabrication
WO2011062380A2 (fr) Dispositif photovoltaïque solaire
WO2011004943A1 (fr) Panneau de cellules solaires
WO2011043517A1 (fr) Cellule solaire et module comprenant des cellules solaires
WO2011040784A2 (fr) Dispositif solaire photovoltaïque
WO2015056934A1 (fr) Module de cellule solaire
WO2013133634A1 (fr) Module de cellule solaire
KR20190120046A (ko) 광 발전 기와 및 광 발전 시스템
WO2015041437A1 (fr) Module de batterie solaire
WO2012096548A2 (fr) Module de cellules solaires
WO2019083059A1 (fr) Cellule solaire à électrode collectrice marginale et module solaire la comprenant
WO2020204527A1 (fr) Panneau de cellules solaires et son procédé de fabrication
WO2012015108A1 (fr) Panneau de cellules solaires
WO2013162302A1 (fr) Appareil photovoltaïque
US20190363205A1 (en) Roof-mounted Solar Modules Integration Device, Solar Power Vehicle and Encapsulation Method for Modules
WO2020096290A1 (fr) Panneau de cellules solaires de satellite artificiel
WO2013077674A1 (fr) Module de cellule solaire et son procédé de fabrication
WO2018070724A1 (fr) Module de cellule solaire
WO2012046933A1 (fr) Dispositif photovoltaïque solaire et son dispositif de transport
WO2011071226A1 (fr) Module de cellule solaire
US20050166954A1 (en) Solar cell panel
WO2015041463A1 (fr) Module de batterie solaire
WO2022260244A1 (fr) Module de cellule solaire et son procédé de fabrication
WO2012020889A1 (fr) Panneau à cellules solaires

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 19881290

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 19881290

Country of ref document: EP

Kind code of ref document: A1