JPS61202474A - Solar battery array for space - Google Patents
Solar battery array for spaceInfo
- Publication number
- JPS61202474A JPS61202474A JP60042914A JP4291485A JPS61202474A JP S61202474 A JPS61202474 A JP S61202474A JP 60042914 A JP60042914 A JP 60042914A JP 4291485 A JP4291485 A JP 4291485A JP S61202474 A JPS61202474 A JP S61202474A
- Authority
- JP
- Japan
- Prior art keywords
- space
- solar battery
- insulating film
- solar cell
- connectors
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 239000000758 substrate Substances 0.000 claims abstract description 4
- 150000002484 inorganic compounds Chemical class 0.000 claims description 3
- 229910010272 inorganic material Inorganic materials 0.000 claims description 3
- 150000002894 organic compounds Chemical class 0.000 claims description 2
- 239000006059 cover glass Substances 0.000 abstract description 6
- 239000000853 adhesive Substances 0.000 abstract description 4
- 230000001070 adhesive effect Effects 0.000 abstract description 4
- 238000010891 electric arc Methods 0.000 abstract description 4
- 230000005684 electric field Effects 0.000 abstract description 4
- 238000005036 potential barrier Methods 0.000 abstract description 4
- 230000005855 radiation Effects 0.000 abstract description 3
- 239000011248 coating agent Substances 0.000 abstract 1
- 238000000576 coating method Methods 0.000 abstract 1
- 230000002542 deteriorative effect Effects 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 150000002500 ions Chemical class 0.000 description 3
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 2
- 239000004642 Polyimide Substances 0.000 description 1
- JJWKPURADFRFRB-UHFFFAOYSA-N carbonyl sulfide Chemical compound O=C=S JJWKPURADFRFRB-UHFFFAOYSA-N 0.000 description 1
- 230000006866 deterioration Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 229920001721 polyimide Polymers 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 235000012239 silicon dioxide Nutrition 0.000 description 1
- 239000000377 silicon dioxide Substances 0.000 description 1
- 238000001771 vacuum deposition Methods 0.000 description 1
- 230000002747 voluntary effect Effects 0.000 description 1
Classifications
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01L—SEMICONDUCTOR DEVICES NOT COVERED BY CLASS H10
- H01L31/00—Semiconductor devices sensitive to infrared radiation, light, electromagnetic radiation of shorter wavelength or corpuscular radiation and specially adapted either for the conversion of the energy of such radiation into electrical energy or for the control of electrical energy by such radiation; Processes or apparatus specially adapted for the manufacture or treatment thereof or of parts thereof; Details thereof
- H01L31/04—Semiconductor devices sensitive to infrared radiation, light, electromagnetic radiation of shorter wavelength or corpuscular radiation and specially adapted either for the conversion of the energy of such radiation into electrical energy or for the control of electrical energy by such radiation; Processes or apparatus specially adapted for the manufacture or treatment thereof or of parts thereof; Details thereof adapted as photovoltaic [PV] conversion devices
- H01L31/042—PV modules or arrays of single PV cells
- H01L31/05—Electrical interconnection means between PV cells inside the PV module, e.g. series connection of PV cells
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/50—Photovoltaic [PV] energy
Landscapes
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Physics & Mathematics (AREA)
- Condensed Matter Physics & Semiconductors (AREA)
- Electromagnetism (AREA)
- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Computer Hardware Design (AREA)
- Microelectronics & Electronic Packaging (AREA)
- Power Engineering (AREA)
- Photovoltaic Devices (AREA)
Abstract
Description
【発明の詳細な説明】
〔産業上の利用分野〕
本発明は、宇宙飛翔体、宇宙構造物あるいは太陽発電衛
星等の宇宙機器に使用される宇宙用太陽電池アレイに関
する。DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to a space solar cell array used in space vehicles, space structures, or space equipment such as solar power generation satellites.
従来、宇宙機器には、太陽電池から大電力を供給する必
要上、第２図に示すような展開型の翼構造をもつ太陽電
池アレイが備えられたものがある。Conventionally, space equipment has been equipped with a solar cell array having a deployable wing structure as shown in FIG. 2 in order to supply large amounts of power from solar cells.
これを同図および第３図に基づいて説明すると、符号１
で示すものは電力供給用の太陽電池アレイ翼で、飛翔棒
本体２の両側に設けられている。３はインターコネクタ
４によって直列あるいは並列に電気的に接続された多数
の太陽電池セルで、基板５上に接着剤６を介して接合さ
れている。７は透明性を有するカバーガラスで、透明接
着剤８によって前記太陽電池セル３上に接合されており
、宇宙の放射線による太陽電池セル３の劣化を防止し得
るように構成されている。To explain this based on the same figure and FIG. 3, reference numeral 1
What is shown by is a solar cell array wing for power supply, which is provided on both sides of the flight rod main body 2. Reference numeral 3 denotes a large number of solar cells electrically connected in series or in parallel by interconnectors 4, which are bonded onto a substrate 5 via an adhesive 6. Reference numeral 7 denotes a transparent cover glass, which is bonded onto the solar cell 3 with a transparent adhesive 8, and is configured to prevent deterioration of the solar cell 3 due to cosmic radiation.
ところで、このような宇宙用太陽電池アレイにおいては
、宇宙のプラズマ中の電子電流密度が正イオン電流密度
に比べて大きいため、太陽電池アレイ翼１に発生する出
力電圧を■ボルトとすると、平衡条件より太陽電池アレ
イ翼１の電位分布が第４図に示すようにプラズマの平均
電位に対して大きく負に沈むことが知られている。同図
において、９および１０はプラズマ中の正イオンと電子
である。なお、第５図（ａ）および（ｂ）は太陽電池ア
レイ翼１の局部を示す断面図とその電位分布状態を示す
図で、同図において、１１はインターコネクタ４から放
出される電子である。By the way, in such a space solar cell array, since the electron current density in the space plasma is larger than the positive ion current density, if the output voltage generated at the solar cell array wing 1 is volts, then the equilibrium condition is It is known that the potential distribution of the solar cell array blade 1 becomes significantly negative with respect to the average potential of the plasma, as shown in FIG. In the figure, 9 and 10 are positive ions and electrons in the plasma. Note that FIGS. 5(a) and 5(b) are cross-sectional views showing local parts of the solar cell array blade 1 and diagrams showing the state of potential distribution thereof, and in the figures, 11 is an electron emitted from the interconnector 4. .
ところが、従来の宇宙用太陽電池アレイにおいては、イ
ンターコネクタ４が宇宙に露呈する構造であるため、イ
ンターコネクタ４とカバーガラス７との間にアーク放電
が発生する虞れがあった。However, in the conventional space solar cell array, since the interconnector 4 is exposed to space, there is a risk that arc discharge may occur between the interconnector 4 and the cover glass 7.
すなわち、宇宙プラズマとの相互作用によってカバーガ
ラス７の表面上に正イオンが蓄積すると、カバーガラス
７の表面の電位が第４図に示す電位分布をもつインター
コネクタ４の電位に対し正電位となり、このため太陽電
池アレイの出力電圧を高電圧化する場合、その電位差が
一層大きくなるからである。これは、電界強度の高いイ
ンターコネクタ４から電界放出効果によって放出される
電子１１が起因するものと考えられている。That is, when positive ions accumulate on the surface of the cover glass 7 due to interaction with space plasma, the potential on the surface of the cover glass 7 becomes positive with respect to the potential of the interconnector 4, which has the potential distribution shown in FIG. For this reason, when increasing the output voltage of the solar cell array, the potential difference becomes even larger. This is thought to be caused by the electrons 11 emitted by the field emission effect from the interconnector 4, which has a high electric field strength.
本発明はこのような事情に鑑みなされたもので、インタ
ーコネクタとカバ一部材間におけるアーク放電の発生を
防止でき、宇宙機器としての信頼性を向上させることが
できる宇宙用太陽電池アレイを提供するものである。The present invention has been made in view of the above circumstances, and provides a space solar cell array that can prevent arc discharge between an interconnector and a cover member, and can improve reliability as a space device. It is something.
本発明に係る宇宙用太陽電池アレイは、多数の太陽電池
セルを接続するインターコネクタの表面を絶縁膜で被覆
したものである。The space solar cell array according to the present invention is one in which the surface of an interconnector that connects a large number of solar cells is coated with an insulating film.
本発明においては、インターコネクタの表面を絶縁膜で
被覆したから、インターコネクタの表面に電子放出を抑
制できる電位障壁が形成されることになる。In the present invention, since the surface of the interconnector is coated with an insulating film, a potential barrier capable of suppressing electron emission is formed on the surface of the interconnector.
第１図は本発明に係る宇宙用太陽電池アレイを示す、断
面図で、同図において第３図および第５図と同一の部材
については同一の符号を付し、詳細な説明は省略する。FIG. 1 is a cross-sectional view showing a space solar cell array according to the present invention. In this figure, the same members as in FIGS. 3 and 5 are designated by the same reference numerals, and detailed description thereof will be omitted.
同図において、２１は二酸化珪素（ＳｉＯ□）等の無機
化合物よりなる絶縁膜で、真空蒸着法等によって前記イ
ンターコネクタ４の表面に被覆されている。この絶縁膜
２１は、絶縁性のみならず可撓性をもたすために厚さ略
１μｍに形成されることが望ましい。In the figure, 21 is an insulating film made of an inorganic compound such as silicon dioxide (SiO□), which is coated on the surface of the interconnector 4 by vacuum deposition or the like. This insulating film 21 is desirably formed to have a thickness of about 1 μm in order to have not only insulating properties but also flexibility.
このように構成された宇宙用太陽電池アレイにおいては
、インターコネクタ４表面を絶縁膜２１で被覆したから
、太陽電池アレイの高電圧化によりインターコネクタ４
の電界強度が大きくなっても、電子１１の放出を抑制で
きる電位障壁がインターコネクタ４の表面に形成される
ことになる。In the space solar cell array configured as described above, since the surface of the interconnector 4 is coated with the insulating film 21, the interconnector 4 is coated with the high voltage of the solar cell array.
Even if the electric field strength increases, a potential barrier capable of suppressing the emission of electrons 11 is formed on the surface of the interconnector 4.
なお、本実施例においては、絶縁膜２１として無機化合
物からなるものを示したが、本発明はこれに限定される
ものではなく、例えば耐放射性に優れたポリイミド系の
有機化合物からなるものであっても実施例と同様の効果
を奏する。In this embodiment, the insulating film 21 is made of an inorganic compound, but the present invention is not limited to this. For example, the insulating film 21 may be made of a polyimide-based organic compound with excellent radiation resistance. However, the same effects as in the embodiment can be obtained.
また、実施例においては、いわゆるカバード・セル（Ｃ
ｏｖｅｒｅｄ Ｃｅ１ｌ）構造をもつものに適用する
例を示したが、本発明は、その他コネクタ・インテグレ
ーティソド・セル（ＣＩ Ｃ：Ｃｏｎｎｅｃｔｏｒ
Ｉｎｔｅｇｒａｔｅｄ Ｃｅ１ｌ）構造やラップ・ア
ラウンド・セル（ＷＡＣ：Ｗｒａｐ Ａｒｒｏｕｎｄ
Ｃｅ ｌ ｌ）構造をもつものにも適用可能である
。In addition, in the embodiment, a so-called covered cell (C
Although an example has been shown in which the present invention is applied to a connector having an overed Ce1l structure, the present invention is applicable to other
Integrated Ce1l) structure and wrap around cell (WAC) structure
It is also applicable to those having a Cell structure.
以上説明したように本発明によれば、多数の太陽電池セ
ルを接続するインターコネクタの表面を絶縁膜で被覆し
たので、インターコネクタに電子の放出を抑制できる電
位障壁が形成されることになる。したがって、インター
コネクタの電界強度が大きくなっても、アーク放電の発
生を確実に防止でき、宇宙機器としての信頼性を向上さ
せることができる。As explained above, according to the present invention, the surface of the interconnector that connects a large number of solar cells is coated with an insulating film, so that a potential barrier capable of suppressing the emission of electrons is formed in the interconnector. Therefore, even if the electric field strength of the interconnector increases, arc discharge can be reliably prevented from occurring, and the reliability of the space device can be improved.
【図面の簡単な説明】
第１図は本発明に係る宇宙用太陽電池アレイを示す断面
図、第２図は宇宙飛翔体の概略を示す斜視図、第３図は
従来の宇宙用太陽電池アレイを示す断面図、第４図（ａ
）および（ｂ）は太陽電池プレイ翼の概略図とその電位
分布状態を示す図、第５図（ａｌおよび申）は太陽電池
アレイ翼の局部を示す断面図とその電位分布状態を示す
図である。
３・・・・太陽電池セル、４・・・・インターコネクタ
、５・・・・基板、７・・・・カバーガラス、２１・・
・・絶縁膜。
代 理 人 大 岩 増 雄第１図
３：ムＳ電シぜ−こル
４：Ａンター″３をフタ
５：幕板
７：ｆｌ ／Ｓ−Ｊ’ヲス
２１：腓μシ！ＩＬ
！！４図
（ｂ）
手続補正書（自発）
昭和 ６へ“′月１９ 日
ツ[Brief Description of the Drawings] Fig. 1 is a cross-sectional view showing a space solar cell array according to the present invention, Fig. 2 is a perspective view schematically showing a spacecraft, and Fig. 3 is a conventional space solar cell array. 4 (a)
) and (b) are schematic diagrams of the solar cell array blades and diagrams showing their potential distribution states, and Figures 5 (al and 2) are cross-sectional views showing local parts of the solar battery array wings and diagrams showing their potential distribution states. be. 3...Solar battery cell, 4...Interconnector, 5...Substrate, 7...Cover glass, 21...
...Insulating film. Deputy Masuo Daiiwa 1 Figure 3: Mus S electric shield 4: Anter" 3 wo lid 5: Curtain plate 7: fl /S-J'wosu 21: 蓓μし!IL!! Figure 4 (b) Procedural amendment (voluntary) Showa 6 to 19th month
Claims (3)
された多数の太陽電池セルを備えた宇宙用太陽電池アレ
イにおいて、前記インターコネクタの表面を絶縁膜で被
覆したことを特徴とする宇宙用太陽電池アレイ。(1) A space solar cell array comprising a large number of solar cells provided on a substrate and connected by interconnectors, characterized in that the surface of the interconnector is coated with an insulating film. .
項記載の宇宙用太陽電池アレイ。(2) Claim 1 in which the insulating film is made of an inorganic compound
Space solar cell array described in Section 1.
項記載の宇宙用太陽電池アレイ。(3) Claim 1 in which the insulating film is made of an organic compound
Space solar cell array described in Section 1.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP60042914A JPS61202474A (en) | 1985-03-05 | 1985-03-05 | Solar battery array for space |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP60042914A JPS61202474A (en) | 1985-03-05 | 1985-03-05 | Solar battery array for space |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS61202474A true JPS61202474A (en) | 1986-09-08 |
Family
ID=12649287
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP60042914A Pending JPS61202474A (en) | 1985-03-05 | 1985-03-05 | Solar battery array for space |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS61202474A (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0621501A (en) * | 1992-03-31 | 1994-01-28 | Canon Inc | Solar cell module and manufacture thereof |
| US6262358B1 (en) | 1999-02-18 | 2001-07-17 | Sharp Kabushiki Kaisha | Solar cell module and solar cell panel using the same |
| WO2003023868A1 (en) * | 2001-09-10 | 2003-03-20 | Ekla-Tek, Llc | Photovoltaic array and method of manufacturing same |
| DE10230392A1 (en) * | 2002-07-05 | 2004-01-29 | SUNOVATION Gesellschaft für regenerative Energiesysteme mbH | Solar module for directly converting sunlight into electrical energy comprises solar cells with contact electrodes joined together by metal contact bridges which have an electrical conductor provided with a flexible casing |
| JP2005191125A (en) * | 2003-12-24 | 2005-07-14 | Kyocera Corp | Connection tab for connecting solar battery element and solar battery module, and method of manufacturing solar battery module |
| JP2008502149A (en) * | 2004-06-04 | 2008-01-24 | サンパワー コーポレイション | Interconnection of solar cells in solar cell modules |
| JP2011151192A (en) * | 2010-01-21 | 2011-08-04 | Sharp Corp | Solar cell, solar cell with interconnector, and manufacturing method thereof |
| JP2013030770A (en) * | 2011-07-12 | 2013-02-07 | Astrium Gmbh | Solar cell and solar cell assembly |
| JP2018082152A (en) * | 2016-09-14 | 2018-05-24 | ザ・ボーイング・カンパニーＴｈｅ Ｂｏｅｉｎｇ Ｃｏｍｐａｎｙ | Solar cell array connection using corner conductor |
| JP2018113440A (en) * | 2017-01-11 | 2018-07-19 | エルジー エレクトロニクス インコーポレイティド | Solar cell module and portable charger comprising the same |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5792873A (en) * | 1980-11-29 | 1982-06-09 | Toshiba Corp | Solar battery panel and manufacture of the same |
| JPS58219779A (en) * | 1982-05-28 | 1983-12-21 | アンプ・インコ−ポレ−テツド | Light voltage generating module and method of producing same |
-
1985
- 1985-03-05 JP JP60042914A patent/JPS61202474A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5792873A (en) * | 1980-11-29 | 1982-06-09 | Toshiba Corp | Solar battery panel and manufacture of the same |
| JPS58219779A (en) * | 1982-05-28 | 1983-12-21 | アンプ・インコ−ポレ−テツド | Light voltage generating module and method of producing same |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0621501A (en) * | 1992-03-31 | 1994-01-28 | Canon Inc | Solar cell module and manufacture thereof |
| US6262358B1 (en) | 1999-02-18 | 2001-07-17 | Sharp Kabushiki Kaisha | Solar cell module and solar cell panel using the same |
| WO2003023868A1 (en) * | 2001-09-10 | 2003-03-20 | Ekla-Tek, Llc | Photovoltaic array and method of manufacturing same |
| US6555739B2 (en) | 2001-09-10 | 2003-04-29 | Ekla-Tek, Llc | Photovoltaic array and method of manufacturing same |
| DE10230392A1 (en) * | 2002-07-05 | 2004-01-29 | SUNOVATION Gesellschaft für regenerative Energiesysteme mbH | Solar module for directly converting sunlight into electrical energy comprises solar cells with contact electrodes joined together by metal contact bridges which have an electrical conductor provided with a flexible casing |
| DE10230392B4 (en) * | 2002-07-05 | 2004-12-02 | SUNOVATION Gesellschaft für regenerative Energiesysteme mbH | Solar module for the direct conversion of sunlight into electrical energy |
| JP2005191125A (en) * | 2003-12-24 | 2005-07-14 | Kyocera Corp | Connection tab for connecting solar battery element and solar battery module, and method of manufacturing solar battery module |
| JP2008502149A (en) * | 2004-06-04 | 2008-01-24 | サンパワー コーポレイション | Interconnection of solar cells in solar cell modules |
| JP2011151192A (en) * | 2010-01-21 | 2011-08-04 | Sharp Corp | Solar cell, solar cell with interconnector, and manufacturing method thereof |
| JP2013030770A (en) * | 2011-07-12 | 2013-02-07 | Astrium Gmbh | Solar cell and solar cell assembly |
| JP2018082152A (en) * | 2016-09-14 | 2018-05-24 | ザ・ボーイング・カンパニーＴｈｅ Ｂｏｅｉｎｇ Ｃｏｍｐａｎｙ | Solar cell array connection using corner conductor |
| JP2023002572A (en) * | 2016-09-14 | 2023-01-10 | ザ・ボーイング・カンパニー | Solar cell array connections using corner conductors |
| JP2018113440A (en) * | 2017-01-11 | 2018-07-19 | エルジー エレクトロニクス インコーポレイティド | Solar cell module and portable charger comprising the same |
| CN108336174A (en) * | 2017-01-11 | 2018-07-27 | Lg电子株式会社 | Solar cell module and portable charger |
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