JPS6145600B2 - - Google Patents
Info
- Publication number
- JPS6145600B2 JPS6145600B2 JP55170062A JP17006280A JPS6145600B2 JP S6145600 B2 JPS6145600 B2 JP S6145600B2 JP 55170062 A JP55170062 A JP 55170062A JP 17006280 A JP17006280 A JP 17006280A JP S6145600 B2 JPS6145600 B2 JP S6145600B2
- Authority
- JP
- Japan
- Prior art keywords
- optical system
- sunlight
- spacecraft
- power supply
- optical
- 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.)
- Expired
Links
- 230000003287 optical effect Effects 0.000 claims description 16
- 239000013307 optical fiber Substances 0.000 claims description 5
- 230000017525 heat dissipation Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000005855 radiation Effects 0.000 description 2
- JJWKPURADFRFRB-UHFFFAOYSA-N carbonyl sulfide Chemical compound O=C=S JJWKPURADFRFRB-UHFFFAOYSA-N 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
Classifications
-
- H—ELECTRICITY
- H10—SEMICONDUCTOR DEVICES; ELECTRIC SOLID-STATE DEVICES NOT OTHERWISE PROVIDED FOR
- H10F—INORGANIC SEMICONDUCTOR DEVICES SENSITIVE TO INFRARED RADIATION, LIGHT, ELECTROMAGNETIC RADIATION OF SHORTER WAVELENGTH OR CORPUSCULAR RADIATION
- H10F77/00—Constructional details of devices covered by this subclass
- H10F77/40—Optical elements or arrangements
- H10F77/42—Optical elements or arrangements directly associated or integrated with photovoltaic cells, e.g. light-reflecting means or light-concentrating means
-
- 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
- Y02E10/52—PV systems with concentrators
Landscapes
- Photovoltaic Devices (AREA)
Description
【発明の詳細な説明】
本発明は人工衛星等の宇宙飛行体に於て使用さ
れる電源装置に関するものである。DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a power supply device used in a space vehicle such as an artificial satellite.
一般に、人工衛星等の宇宙飛行体に於ては、必
要となるエネルギーを太陽電池を利用して太陽の
光エネルギーを電気エネルギーに変換することに
より得ることが行われている。ところが、太陽電
池には、宇宙間に存在する放射線の入射により、
次第に性能が劣化すると共に、太陽光線の入射に
依り温度が上昇し、光電変換効率が低下するとい
う欠点がある。このため従来は太陽電池の表面に
光学フイルタを蒸着した光学材料板をカバーとし
て装着していた。このカバーの製作及び実装は極
めて高価格であり、電源系全体を高価格にすると
いう欠点があつた。また、太陽電池を太陽光の照
射を受けるために、人工衛星等の外部に装着する
ことが必要となることから、人工衛星等の形状及
び構造決定上に大きな制約を生じる欠点があつ
た。 Generally, in space vehicles such as artificial satellites, necessary energy is obtained by converting sunlight energy into electrical energy using solar cells. However, due to the incidence of radiation existing in space, solar cells
The disadvantage is that the performance gradually deteriorates, and the temperature rises due to the incidence of sunlight, resulting in a decrease in photoelectric conversion efficiency. For this reason, conventionally, an optical material plate with an optical filter deposited on the surface of the solar cell was attached as a cover. The manufacturing and mounting of this cover is extremely expensive and has the drawback of making the entire power supply system expensive. In addition, since it is necessary to attach the solar cell to the outside of the artificial satellite in order to receive sunlight irradiation, there is a drawback that there is a large restriction in determining the shape and structure of the artificial satellite.
本発明は、これらの欠点を除去し、太陽電池を
人工衛星等の本体内に収容し、太陽光を光学系及
び光フアイバー素子を介して入射させるようにし
た電源装置にある。 The present invention eliminates these drawbacks and provides a power supply device in which a solar cell is housed in a main body of an artificial satellite or the like, and sunlight is made incident through an optical system and an optical fiber element.
以下、図面により本発明を詳細に説明する。 Hereinafter, the present invention will be explained in detail with reference to the drawings.
第１図は本発明の実施例の構成図であつて、１
は人工衛星等宇宙飛行体の本体、２はこの本体１
と機械的に結合され太陽方向を追尾するとともに
太陽光を集束する機能を有する光学系、４は光を
投射する機能を有する光学系、３は光学系２，４
間を結ぶ光フアイバ、５は太陽電池電源、６は宇
宙暗黒面に対面する熱発散部である。 FIG. 1 is a configuration diagram of an embodiment of the present invention, 1
is the main body of a spacecraft such as an artificial satellite, 2 is this main body 1
4 is an optical system that is mechanically coupled to the optical system and has a function of tracking the direction of the sun and focusing sunlight; 4 is an optical system that has a function of projecting light; 3 is an optical system 2, 4
5 is a solar battery power source, and 6 is a heat dissipation part facing the dark side of space.
この、光学系２に入射した太陽光は光学的に集
束され、光フアイバ３により、光学系４に伝送さ
れ、太陽電池電源５の表面に投射され電気エネル
ギーとして取り出される。この熱発散部６は太陽
光を受けることがないため、常に低温に保たれて
おり、これに装着される太陽電池電源５は効率の
良い低温領域にて動作すると共に、人工衛星等の
本体１の構造体及び熱発散部のしやへい効果に依
り宇宙放射線からも保護される。 This sunlight that has entered the optical system 2 is optically focused, transmitted to the optical system 4 through the optical fiber 3, projected onto the surface of the solar battery power source 5, and extracted as electrical energy. Since this heat dissipation unit 6 does not receive sunlight, it is always kept at a low temperature, and the solar battery power supply 5 attached to it operates in an efficient low temperature region, and the main body 1 of the artificial satellite etc. It is also protected from cosmic radiation due to the shielding effect of its structure and heat dissipating parts.
また、光学系を適切に設定することにより、従
来の方式に比べて太陽電池の面積を縮少すること
が可能となる。 Furthermore, by appropriately setting the optical system, it is possible to reduce the area of the solar cell compared to conventional systems.
以上の説明のとおり、本発明により人工衛生等
の宇宙飛行体に利用される太陽電池の有効寿命を
延長できるばかりでなく、必要枚数を減少して電
源系の価格を低減でき、太陽電池の装着個所に対
する自由度を増加して人工衛生等の設計を容易に
しうる効果がある。 As explained above, the present invention not only extends the effective lifespan of solar cells used in space vehicles such as artificial sanitary vehicles, but also reduces the cost of the power supply system by reducing the number of solar cells required. This has the effect of increasing the degree of freedom for locations and facilitating the design of artificial hygiene.
第１図は本発明の実施例の構成図である。図に
おいて、
１……人工衛星等宇宙飛行体の本体、２……本
体１と機械的に結合され太陽方向を追尾するとと
もに太陽光を集束する機能を有する光学系、３…
…光フアイバ、４……光を投射する機能を有する
光学系、５……太陽電池電源、６……熱発散部、
である。
FIG. 1 is a block diagram of an embodiment of the present invention. In the figure, 1... The main body of a spacecraft such as an artificial satellite, 2... An optical system that is mechanically coupled to the main body 1 and has the function of tracking the direction of the sun and focusing sunlight, 3...
...Optical fiber, 4... Optical system having a function of projecting light, 5... Solar battery power supply, 6... Heat dissipation section,
It is.
Claims (1)
しその太陽光を集光する第１の光学系と、この第
１の光学系の太陽光を前記宇宙飛行体の内部に導
く光フアイバと、この光フアイバからの光を投射
する第２の光学系と、この第２の光学系からの光
を照射され前記宇宙飛行体内部に配置される太陽
電池電源とを含む宇宙飛行体用電源装置。1. A first optical system fixed outside the spacecraft that tracks the direction of the sun and focuses the sunlight, and an optical fiber that guides the sunlight of the first optical system into the inside of the spacecraft. A power supply device for a spacecraft, including a second optical system that projects light from the optical fiber, and a solar cell power source that is irradiated with the light from the second optical system and is disposed inside the spacecraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP55170062A JPS5793583A (en) | 1980-12-02 | 1980-12-02 | Power source for spacecraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP55170062A JPS5793583A (en) | 1980-12-02 | 1980-12-02 | Power source for spacecraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS5793583A JPS5793583A (en) | 1982-06-10 |
| JPS6145600B2 true JPS6145600B2 (en) | 1986-10-08 |
Family
ID=15897916
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP55170062A Granted JPS5793583A (en) | 1980-12-02 | 1980-12-02 | Power source for spacecraft |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS5793583A (en) |
Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS59874A (en) * | 1982-06-26 | 1984-01-06 | Hiroshi Kubota | Irradiating method of light to photochemical reactor |
| JPS59126681A (en) * | 1983-01-11 | 1984-07-21 | Takashi Mori | solar cell device |
| JPS59228772A (en) * | 1983-06-10 | 1984-12-22 | Nec Corp | Solar battery power source |
| JPS6131747A (en) * | 1984-07-24 | 1986-02-14 | Toyota Motor Corp | Speed control method for automatic transmission of vehicle |
| JPS61235298A (en) * | 1985-04-11 | 1986-10-20 | 三菱電機株式会社 | Power generator for artificial satellite |
| US5089055A (en) * | 1989-12-12 | 1992-02-18 | Takashi Nakamura | Survivable solar power-generating systems for use with spacecraft |
| US4976789A (en) * | 1989-12-26 | 1990-12-11 | The United States Of America As Represented By The Secretary Of The Army | Power transmission device |
| WO2021053377A1 (en) * | 2019-09-20 | 2021-03-25 | Abdul Jabbar Abdulla Ali Gargash | A solar power generator |
-
1980
- 1980-12-02 JP JP55170062A patent/JPS5793583A/en active Granted
Also Published As
| Publication number | Publication date |
|---|---|
| JPS5793583A (en) | 1982-06-10 |
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