JPS61226400A - Solar-cell panel device for triaxial control satellite - Google Patents
Solar-cell panel device for triaxial control satelliteInfo
- Publication number
- JPS61226400A JPS61226400A JP60066771A JP6677185A JPS61226400A JP S61226400 A JPS61226400 A JP S61226400A JP 60066771 A JP60066771 A JP 60066771A JP 6677185 A JP6677185 A JP 6677185A JP S61226400 A JPS61226400 A JP S61226400A
- Authority
- JP
- Japan
- Prior art keywords
- satellite
- solar
- panel device
- solar cell
- cell 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
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】
〔発明の技術分野〕
この発明は、電力を効率的に得るようにした３軸制御術
里の太陽電池パネル装置に関する。DETAILED DESCRIPTION OF THE INVENTION [Technical Field of the Invention] The present invention relates to a solar cell panel device with three-axis control that efficiently obtains electric power.
一般に、この種の太陽電池パネル装置は第５図に示すよ
うに、衛星Ｊが軌道上に到達すると、収納されていた太
陽電池パネル２が展開され、以後、この太陽電池ｔ４ネ
ル２が回転駆動部３によって、太陽４に対向されて最大
電力を得て、衛星１の各機器に電力を供給するようにな
って−する。Generally, in this type of solar panel device, as shown in FIG. 5, when the satellite J reaches the orbit, the stored solar panel 2 is deployed, and from then on, this solar panel t4 panel 2 is driven to rotate. The unit 3 faces the sun 4 to obtain maximum power and supply power to each device of the satellite 1.
ところが、上記３軸制御衛星の太陽電池パネル装置では
、その構成上太陽電池ｉ４ネル２を回転制御する回転駆
動部３ｔ−要する。このため、構造が複雑化して重量が
嵩むとともに、故障が ′多く、信頼性が劣ると
いう問題を有している。However, the solar panel device for the three-axis control satellite requires a rotation drive unit 3t for controlling the rotation of the solar cell i4 channel 2 due to its configuration. For this reason, the structure becomes complicated and the weight increases, and there are problems such as frequent failures and poor reliability.
！念、太陽電池／ｆネル２で得た電力を供給する手段と
して、スリップリング（図示せず）などを備えるために
、衛星１の打ち上げ前の状態において酸化され、接触不
良を起こすおそれを有している。! As a means of supplying the power obtained from the solar cell/f-channel 2, there is a risk that slip rings (not shown) may be oxidized and cause poor contact before the satellite 1 is launched. ing.
さらに、軌道上において、太陽電池／ｌネル２の回転に
ともなって外乱トルクが発生し、衛星１の３軸姿勢制御
に悪影響き及ぼすという問題も有している。Furthermore, there is also the problem that disturbance torque is generated as the solar cell/l channel 2 rotates in orbit, which adversely affects the three-axis attitude control of the satellite 1.
この発明は上記従来の欠点を除去するためになされ念も
ので、太陽電池パネルを回転制御することなく、電力を
効率的に得るようにできる３軸制御衛星の太陽電池パネ
ル装置を提供することｔ目的とする。The present invention has been made in order to eliminate the above-mentioned conventional drawbacks, and provides a solar panel device for a three-axis controlled satellite that can efficiently obtain electric power without controlling the rotation of the solar panel. purpose.
この発明の３軸制御衛星の太陽電池パネル装置は、折り
畳み式で収納されかつ略「＋」字状に展開される太陽電
池・ぐネル分保持手段と介して衛星構体に支持し、衛星
構体が軌道にのると展開手段で太陽電池・セネルを略「
＋」字状に展開させるようにしたものである。The solar panel device for a 3-axis controlled satellite of the present invention is foldable and stored, and is supported on the satellite structure via a solar cell/gunnel holding means that is unfolded in a substantially "+" shape. Once in orbit, the deployment means will be used to deploy a solar cell or Senel.
It is designed to develop into a ``+'' shape.
以下、この発明の３軸制御衛星の太陽電池ノ母ネル装置
の実施例について図面に基づき説明する。第１図はこの
発明による３軸制御衛星の太陽電池パネル装置の一実施
例の展開前であり、第２図および第３図はそれぞれ展開
途中および展開後の各状態を示す図である。DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, embodiments of a solar cell bus channel device for a three-axis controlled satellite according to the present invention will be described with reference to the drawings. FIG. 1 shows an embodiment of a solar panel device for a three-axis controlled satellite according to the present invention before deployment, and FIGS. 2 and 3 show states during and after deployment, respectively.
この第１図ないし第３図において、ＩＱは衛星構体であ
る。この衛星構体１０の両端部にはそれぞれ折り畳み自
在な、太陽電池パネル１１゜１４．１５，１７が配設さ
れている。この太陽電池パネル１１．１４〜１７はその
一方端が、上記衛星構体１０に保持機構１２を介在して
支持されておし、保持機構１２によって衛星構体１０に
対して太陽電池／４’ネル１１．１４〜１７の一方端が
略平行な状態で保持するようになっている。In FIGS. 1 to 3, IQ is a satellite structure. At both ends of the satellite structure 10, foldable solar panels 11, 14, 15 and 17 are arranged, respectively. One end of the solar battery panels 11.14 to 17 is supported by the satellite structure 10 through a holding mechanism 12. .14 to 17 are held in a substantially parallel state.
各太陽電池パネル１１．１４〜１７は表裏両側に太陽電
池パネルが配設されている。各太陽電池セルｙ１１．１
４〜１７は展開機構１３によって「＋」字形に展開おる
いは折り畳み可能になっている。なお、１８はアンテナ
リフレクタ、１９はフィードホーンである。Each of the solar panels 11, 14 to 17 is provided with solar panels on both the front and back sides. Each solar cell y11.1
4 to 17 can be unfolded or folded into a "+" shape by the unfolding mechanism 13. Note that 18 is an antenna reflector, and 19 is a feed horn.
次に、以上のように構成され念この発明の３軸制御衛星
の太陽電池・場ネルの動作について説明する。Next, the operation of the solar cell/field channel of the three-axis controlled satellite of the present invention constructed as described above will be explained.
衛星が打ち上げられて軌道上に到達するまで第１図に示
すように太陽電池ノ４ネル１１．１４〜１７が保持機構
１２によって衛星構体１０に対して略平行に折り畳まれ
た状態でパネル固定部２０によって収納保持されている
。Until the satellite is launched and reaches the orbit, the solar cell panels 11, 14 to 17 are folded approximately parallel to the satellite structure 10 by the holding mechanism 12, as shown in FIG. It is stored and held by 20.
衛星が軌道上に到達すると、太陽電池ｉ４ネル装置は地
上からのコマンド信号によって、まず上記パネル固定部
２０が作動し、図示しないスプリング機構によって上記
保持機構１２が反転されて衛星構体１０に対して立設さ
れる。When the satellite reaches orbit, the solar cell i4 channel device first operates the panel fixing part 20 in response to a command signal from the ground, and the holding mechanism 12 is reversed by a spring mechanism (not shown) to be attached to the satellite structure 10. It will be erected.
次に、太陽電池ノ臂ネル１１．１４，１５゜１６．１７
が順次コマンドにより展開機構部１３が駆動し、図示し
ないスプリング機構によって太陽電池パネル１４〜１７
が略「＋」字形に展開し確立する。Next, solar cell armpit 11.14, 15° 16.17
The unfolding mechanism section 13 is sequentially driven by commands, and the solar battery panels 14 to 17 are moved by a spring mechanism (not shown).
expands into a roughly “+” shape and becomes established.
なお、各太陽電池／’？ネル１１．１４〜１７は２枚背
中合わせで作られ、表裏両側の太陽電池セルが配設され
ているので、どのような向きにおいても太陽光は常に平
均して第４図に示す斜線部と等価な面積に照射される。In addition, each solar cell/'? Panels 11.14 to 17 are made with two panels back to back, and solar cells are placed on both the front and back sides, so no matter the orientation, sunlight is always on average equivalent to the shaded area shown in Figure 4. area is irradiated.
以上のように、この発明の３軸制御衛星の太陽電池ＡＩ
ネル装置によれば、折り畳み自在な略「＋」字状の太陽
電池パネルを軌道上において、衛星構体に立設するよう
に構成したので、太陽電池ｔ４ネルを回転駆動すること
なく効率的に電力を得ることができる。As described above, the solar cell AI of the 3-axis controlled satellite of this invention
According to the NEL device, the foldable solar panel in the shape of a "+" is installed upright on the satellite structure in orbit, so it can efficiently generate electricity without rotating the solar cell t4. can be obtained.
これにともない、従来のように回転駆動部を備えること
がなくなり、可及的に軽量化を促進し得るとともに故障
率が低下されて信頼性を向上できる。Accordingly, unlike in the past, there is no longer a need for a rotary drive unit, and the weight can be reduced as much as possible, and the failure rate can be reduced and reliability can be improved.
また、回転駆動されないので、外乱トルクを発生するこ
とがなくなり、衛星の姿勢制御の向上に寄与し得るもの
である。Furthermore, since it is not rotationally driven, no disturbance torque is generated, which can contribute to improving the attitude control of the satellite.
第１図はこの発明の３軸制御衛星の太陽電池ノ４ネル装
置の展開図、第２図および第３図はそれぞれこの発明の
３軸制御衛星の太陽電池パネル装置の一実施例の展開途
中および展開後の状態を示す図、第４図は同上３軸制御
衛星の太陽電池ノ々ネル装置の太陽光照射面積の説明図
、第５図は従来の３軸制御衛星の太陽電池パネル装置の
構成を示す図である。
１０・・・衛星構体、１１．１４〜１７・・・太陽電池
パネル、１２・・・保持機構、１３・・・展開機構部、
１８・・・アンテナリフレクタ、１９・・・フィードホ
ーン、２０・・・パネル固定部。
出願人代理人 弁理士 鈴 江 武 彦第１図
第４図
第５図Fig. 1 is an exploded view of a solar cell panel device for a 3-axis controlled satellite according to the present invention, and Figs. 2 and 3 show an example of the solar cell panel device for a 3-axis controlled satellite according to the present invention being developed. Figure 4 is an explanatory diagram of the sunlight irradiation area of the solar cell panel device of the 3-axis control satellite as above, and Figure 5 is a diagram showing the state after deployment. FIG. 3 is a diagram showing the configuration. 10... Satellite structure, 11. 14-17... Solar battery panel, 12... Holding mechanism, 13... Deployment mechanism section,
18... Antenna reflector, 19... Feed horn, 20... Panel fixing part. Applicant's representative Patent attorney Takehiko Suzue Figure 1 Figure 4 Figure 5
Claims (1)
陽電池パネルと、この太陽電池パネルを衛星構体に対し
て支持する保持手段と、前記太陽電池パネルを軌道上に
おいて上記衛星構体に立設した状態で略「＋」字状に展
開する展開手段とを具備した３軸制御衛星の太陽電池パ
ネル装置。A solar battery panel that is foldable and unfolded in a substantially "+" shape, a holding means that supports the solar panel with respect to the satellite structure, and a holding means that supports the solar battery panel on the satellite structure while in orbit. A solar battery panel device for a three-axis controlled satellite, which is equipped with a deployment means that deploys in a substantially "+" shape when the satellite is installed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP60066771A JPS61226400A (en) | 1985-03-30 | 1985-03-30 | Solar-cell panel device for triaxial control satellite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP60066771A JPS61226400A (en) | 1985-03-30 | 1985-03-30 | Solar-cell panel device for triaxial control satellite |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS61226400A true JPS61226400A (en) | 1986-10-08 |
Family
ID=13325465
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP60066771A Pending JPS61226400A (en) | 1985-03-30 | 1985-03-30 | Solar-cell panel device for triaxial control satellite |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS61226400A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2012501556A (en) * | 2008-09-02 | 2012-01-19 | クォルコム・メムズ・テクノロジーズ・インコーポレーテッド | Light collection device having prismatic light turning features |
-
1985
- 1985-03-30 JP JP60066771A patent/JPS61226400A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2012501556A (en) * | 2008-09-02 | 2012-01-19 | クォルコム・メムズ・テクノロジーズ・インコーポレーテッド | Light collection device having prismatic light turning features |
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