JPS58174100A - Unfolding system of panel of solar cell - Google Patents
Unfolding system of panel of solar cellInfo
- Publication number
- JPS58174100A JPS58174100A JP57054856A JP5485682A JPS58174100A JP S58174100 A JPS58174100 A JP S58174100A JP 57054856 A JP57054856 A JP 57054856A JP 5485682 A JP5485682 A JP 5485682A JP S58174100 A JPS58174100 A JP S58174100A
- Authority
- JP
- Japan
- Prior art keywords
- solar cell
- satellite
- cell panel
- cylindrical
- panel
- 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
Classifications
-
- 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
- Photovoltaic Devices (AREA)
Abstract
(57)【要約】本公報は電子出願前の出願データであるた
め要約のデータは記録されません。(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.
Description
【発明の詳細な説明】
本発明は、宇宙環境下で人工衛星の電力取得に用いる太
陽電池のパネルＮ開方式に関する。DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a solar cell panel N-opening method used for obtaining power for an artificial satellite in a space environment.
従来のスピン形衛屋では、太陽電池パネルの収納方法等
に問題があった友め、はぼ衛星の太きｉ！ＳＫより太陽
電池パネルの大きさが決定され、それに合う電力しか得
られないという欠点があった。With conventional spin-type stores, there were problems with how to store the solar panels, etc., and the thick i! The drawback was that the size of the solar panel was determined by SK, and only the power that matched the size could be obtained.
本発明の目的は、大きさく制約のあるスピン衛星にシい
て、大電力を得、衛星の決められたミッション寿命にお
いてできるだけ多くの機器を動作させることのできる太
陽電池のパネル展開方式を提供することにある。The purpose of the present invention is to provide a method for deploying solar cell panels that can obtain large amounts of power and operate as many devices as possible during the fixed mission life of the satellite for a spin satellite with size constraints. It is in.
前記目的を達成するために本発明による太陽電池のパネ
ル展開方式は４角形状の太陽電池パネルの対辺を結合し
て太陽電池パネル円筒部を形成し、この円筒部２以上を
スピン衛１の外周部に重ね合せるように取付けることに
より太陽電池の各構成要素となる前記各円筒部を衛星内
蔵の駆動モータによシ衛屋の下方に引き伸ばし。In order to achieve the above object, the solar cell panel deployment method according to the present invention connects the opposite sides of a quadrangular solar cell panel to form a cylindrical portion of the solar cell panel, and connects two or more of these cylindrical portions to the outer periphery of the spin guard 1. By attaching the cylindrical parts to the parts so as to overlap each other, each of the cylindrical parts, which are the constituent elements of the solar cell, is stretched downwards by the drive motor built into the satellite.
この引き伸ばした各円筒部を形成して込る分一部を分離
装置により分離し、各円筒部の端部に取プ付けられた伸
展棒を横方向に伸ばすことにより、それぞれ各円筒部を
展開し、所定平面形状の太陽電池パネルを形成するよう
に構成しである。A separation device separates the part that forms each stretched cylindrical part, and each cylindrical part is expanded by horizontally extending the extension rod attached to the end of each cylindrical part. However, it is configured to form a solar cell panel having a predetermined planar shape.
前記構成によれば本発明の目的を完全に達成することが
できる。According to the above configuration, the object of the present invention can be completely achieved.
以下、図面等を参照して本発明をさらに詳しく説明する
。第１図は本発明による展開方式を適用したスピン衛星
の斜視図で、２つの太陽電池パネル円筒部２ａ、ｊｅｂ
を取付けた例である。Hereinafter, the present invention will be explained in more detail with reference to the drawings and the like. FIG. 1 is a perspective view of a spin satellite to which the deployment method according to the present invention is applied, in which two solar panel cylinders 2a and jeb
This is an example of installing.
各円筒部２鳳、２ｂは長方形状のパネルの対辺の一部（
この例では上端と下端の２ケ所）を結合することによっ
て形成されており、その結合部は分離装置４ａ、４ｂに
より切離されるようになっている。各円筒部ｚ ａ 、
Ｔｔ ｂ ０ｇ１ｌｉｉＫは駆動装置１ｍ、ｌｂと伸
展部３＠、３ｂが取付けられている。Each cylindrical part 2b is a part of the opposite side of the rectangular panel (
In this example, it is formed by joining two parts (an upper end and a lower end), and the joined parts are separated by separation devices 4a and 4b. Each cylindrical part z a ,
Tt b 0g1liiK is equipped with drive devices 1m, lb and extension parts 3@, 3b.
第２図は太陽電池パネル円筒部２ｍ、２ｂをスピン衛星
の下方に引き伸ばし要因である。この引き伸ばしＫはス
ピン衛星内蔵のモータが使用される。各円筒部２ａ、２
ｂが完全に引き出されるとその後は分離装置４ｍ、４ｂ
Ｋより円筒部２ｍ、Ｗｂの上端と下端が分離され、展開
可能となる。なお、このときの分離は円筒部Ｚａ。FIG. 2 shows the factors that cause the solar panel cylindrical parts 2m and 2b to be stretched below the spin satellite. This stretching K uses a motor built into the spin satellite. Each cylindrical part 2a, 2
When b is completely pulled out, the separation devices 4m and 4b
The upper and lower ends of the cylindrical portion 2m and Wb are separated from K and can be expanded. Note that the separation at this time is the cylindrical portion Za.
２ｂの順番で行なわれる。2b.
第３図は各円Ｉ１１部を展開した図である。上下指部が
分離された後は駆動装置１ ａ ＃ １ ｂによｐ伸展
棒ｓｍ、３ｂが引き出され、各円筒部２ｍ５２ｂが第３
図に示すように展開される。FIG. 3 is an expanded view of the I11 portion of each circle. After the upper and lower finger parts are separated, the p extension rods m and 3b are pulled out by the drive device 1a #1b, and each cylindrical part 2m52b is
It is expanded as shown in the figure.
第４図は第３図の伸展部の詳細を示す図であるＯ伸展部
は駆動モータ８．歯車９．ワイヤ１０．支点棒１１およ
び伸展部３−１．３−２．・・・・・・３−５よシ構成
されている。ワイヤエ０はその一端が３−１の支点棒に
固定され、３−４．３−３゜３−２．３−１の各歯車と
支点棒を経由して駆動モータ８に巻堆られるようになっ
て込る。歯車９は１の位置から１′の位置に、３−鵞の
歯車はｂの位置からｂ′の位置に、以下、各歯車につい
てＣはＣ′、ｄはｄ′にそれぞれ移動可能になってＡる
。したがって駆動モータ８を回転させると、各伸展部３
−１．３−冨、Ｓ−３゜３−４．３−８の各歯車は順番
に”ＺｂＺＣ’ａｄ′ の位置に移動し、伸展する仕組
みになっている。FIG. 4 is a diagram showing details of the extension section in FIG. 3. The extension section is driven by a drive motor 8. Gear 9. Wire 10. Fulcrum rod 11 and extension portion 3-1.3-2. ...It is composed of 3-5. One end of the wire 0 is fixed to the fulcrum rod 3-1, and it is wound onto the drive motor 8 via the gears 3-4.3-3 and 3-2.3-1 and the fulcrum rod. It's getting complicated. Gear 9 can be moved from position 1 to position 1', gear 3 can be moved from position b to position b', and for each gear C can be moved to C' and d can be moved to d'. Aru. Therefore, when the drive motor 8 is rotated, each extension part 3
-1.3-Fuji, S-3゜3-4. Each gear of 3-8 sequentially moves to the position ``ZbZC'ad'' and extends.
第Ｓ図はこのように展開した太陽電池ノ（ネルが搭載さ
れたスピン衛星と太陽の関係を示し要因である。展開さ
れて平面形状となった太陽電池パネル２１．Ｗｂは常に
太陽１４の方向に向くように制御される。Figure S shows the relationship between the sun and the spin satellite on which the solar cell panel 21. controlled to point towards.
以上、詳しく説明し九ように本発明によれば、スピン衛
星の大きさに制約を受けることなく。As described above in detail, according to the present invention, there is no restriction on the size of the spin satellite.
大容量の太陽電池パネルを構成することができるので、
搭載機器の要求に応じて大電力を供給することが可能と
なる。Since it is possible to construct large-capacity solar panels,
It becomes possible to supply large amounts of power according to the demands of onboard equipment.
第１図は本発明による太陽電池のパネル展開方式を適用
したスピン衛星の斜視図、第２図は太陽電池パネル展開
過程を示すスピン衛星の斜視図、第３図は太陽電池パネ
ルが展開されたスピン衛星の斜視図、４４図は伸展部の
詳細図、第！１図は本発明方式を適用したスピン衛星と
太陽との位置関係を示す図である。
ｌａ、１ｂａ）・・・駆動装置
２ａｓ２ｂ・・・太陽電池ノくネル
３ｍ、３ｂ・・・伸展部 ４ｇ、４ｂ・・・分離装置
Ｓ−・・ディスパンモータ ６・・・衛星本体部ト・・
駆動モータ ９・・・歯車１０・・・ワイヤ
１１・・・支点棒１２・・・スピン衛星 １３
ａ、 １３ｂ・・・ドラム１４・・・太陽
工５・・・地球特許出願人 日本電気株式会社
代理人 弁理士 井 ノ ロ 壽Fig. 1 is a perspective view of a spin satellite to which the solar cell panel deployment method according to the present invention is applied, Fig. 2 is a perspective view of a spin satellite showing the solar cell panel deployment process, and Fig. 3 is a perspective view of the spin satellite with the solar battery panel deployed. A perspective view of the spin satellite, Figure 44 is a detailed view of the extension part, and Figure 44 is a detailed view of the extension part. FIG. 1 is a diagram showing the positional relationship between a spin satellite to which the method of the present invention is applied and the sun. la, 1ba)...Drive device 2as2b...Solar cell nozzle 3m, 3b...Extension part 4g, 4b...Separation device S-...Dispan motor 6...Satellite body part...・
Drive motor 9...Gear 10...Wire
11...Fullin rod 12...Spin satellite 13
a, 13b...drum 14...sun
Engineering 5...Global Patent Applicant NEC Corporation Representative Patent Attorney Hisashi Inoro
Claims (1)
ネル円筒部を形成し、この円筒部２以上をスピン衛星の
外周部に重ね合せるように取付けることにより太陽電池
の各構成要素となる前記各円筒部を衛星内蔵の駆動モー
タにより衛星の下方（引き伸ばし、この引き伸ばした各
円筒部を形成している分離部を分離装置により分離し、
各円筒部の端部に取り付けられた伸展棒を横方向に伸ば
すことにより、それぞれ各円筒部を展開し、所定平面形
状の太陽電池パネルを形成することを特徴とする太陽電
池のパネル展開方式。Opposite sides of a square solar cell panel are joined to form a solar cell panel cylindrical portion, and two or more of these cylindrical portions are attached to overlap the outer circumference of a spin satellite, thereby forming each component of a solar cell. Each cylindrical part is stretched below the satellite by a drive motor built into the satellite, and the separating parts forming each stretched cylindrical part are separated by a separating device.
A solar cell panel deployment method characterized in that each cylindrical portion is expanded by horizontally extending an extension rod attached to an end of each cylindrical portion to form a solar cell panel having a predetermined planar shape.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP57054856A JPS58174100A (en) | 1982-04-02 | 1982-04-02 | Unfolding system of panel of solar cell |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP57054856A JPS58174100A (en) | 1982-04-02 | 1982-04-02 | Unfolding system of panel of solar cell |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS58174100A true JPS58174100A (en) | 1983-10-13 |
Family
ID=12982229
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP57054856A Pending JPS58174100A (en) | 1982-04-02 | 1982-04-02 | Unfolding system of panel of solar cell |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS58174100A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2000003441A1 (en) * | 1998-07-08 | 2000-01-20 | Misawa Homes Co., Ltd. | Solar battery unit and solar battery device |
| CN105674001A (en) * | 2016-03-16 | 2016-06-15 | 中国科学院西安光学精密机械研究所 | Telescopic stretchable mechanism |
-
1982
- 1982-04-02 JP JP57054856A patent/JPS58174100A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2000003441A1 (en) * | 1998-07-08 | 2000-01-20 | Misawa Homes Co., Ltd. | Solar battery unit and solar battery device |
| US6346669B1 (en) | 1998-07-08 | 2002-02-12 | Misawa Homes Co., Ltd. | Solar battery unit and solar battery apparatus |
| CN105674001A (en) * | 2016-03-16 | 2016-06-15 | 中国科学院西安光学精密机械研究所 | Telescopic stretchable mechanism |
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