JPS58188800A - Unfolding mechanism of unfolding type solar cell paddle - Google Patents
Unfolding mechanism of unfolding type solar cell paddleInfo
- Publication number
- JPS58188800A JPS58188800A JP58056784A JP5678483A JPS58188800A JP S58188800 A JPS58188800 A JP S58188800A JP 58056784 A JP58056784 A JP 58056784A JP 5678483 A JP5678483 A JP 5678483A JP S58188800 A JPS58188800 A JP S58188800A
- Authority
- JP
- Japan
- Prior art keywords
- spiral spring
- unfolding
- hinge
- solar cell
- sleeve
- 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.)
- Granted
Links
- DSSYKIVIOFKYAU-XCBNKYQSSA-N (R)-camphor Chemical compound C1C[C@@]2(C)C(=O)C[C@@H]1C2(C)C DSSYKIVIOFKYAU-XCBNKYQSSA-N 0.000 description 1
- 241000723346 Cinnamomum camphora Species 0.000 description 1
- 229960000846 camphor Drugs 0.000 description 1
- 229930008380 camphor Natural products 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
Classifications
-
- 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
- B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
- B64G1/2221—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state characterised by the manner of deployment
- B64G1/2222—Folding
-
- 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
-
- 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
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Photovoltaic Devices (AREA)
- Pivots And Pivotal Connections (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】
この発明は、表面に太陽電池セルが貼られたパネルを使
用時に確実に展開する展開型太陽電池パドルの展開機構
に関するものである。DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a deployment mechanism for a deployable solar battery paddle that reliably deploys a panel having solar battery cells pasted on its surface during use.
従来、この種の展開機構としては、ｗｃ１図〜第５図に
示すようなものがあった。図において、（１１（２１は
その表面に太陽電池セル（図示せず］が貼られ九ハネル
、（３）はパネル（１）のコーナ一部に取付けられたク
レビス金具、（（転）は前記クレビス金具（３）と一体
であるヒンジビン、（６）は前記パネル（２）のコーナ
一部に取付けられたクレビス金具、（９）は前記ヒンジ
ビン（４）に巻き付けられたねじりコイルバネ、（Ｉ・
は前記ねじりコイルバネ（９）の端部保持具、１１υは
前記クレビス金具（６）と一体となったベアリングであ
って、前記ヒンジビン（４）とベアリング０υの回転自
在な連結により、両パネル（旧２）を使用前は折り畳ん
だ状態とし、使用時には展開した状態とするようになっ
ている。Conventionally, as this type of unfolding mechanism, there have been those shown in wc1 to 5. In the figure, (11 (21) is a nine panel panel with solar cells (not shown) pasted on its surface, (3) is a clevis fitting attached to a part of the corner of panel (1), A hinge bin integrated with the clevis fitting (3), (6) a clevis fitting attached to a part of the corner of the panel (2), (9) a torsion coil spring wound around the hinge bin (4), (I.
11υ is an end holder for the torsion coil spring (9), and 11υ is a bearing integrated with the clevis fitting (6). The rotatable connection between the hinge bin (4) and the bearing 0υ allows both panels (formerly 2) is in a folded state before use, and is in an unfolded state when in use.
次に動作について説明する。Next, the operation will be explained.
第３図に示すように使用前の折り畳んだ状態から太陽電
池パドルの保持解放機構（図示せず）が解放されたなら
ば、ヒンジの一方のクレビス金具（３）と一体のヒンジ
ピン（４）に巻き付けられたねじりコイルバネ（９）の
回転トルクにより太陽電池パドルを展開する。As shown in Figure 3, once the holding and releasing mechanism (not shown) of the solar array paddle is released from the folded state before use, the hinge pin (4) integrated with the clevis fitting (3) on one side of the hinge The solar battery paddle is expanded by the rotational torque of the twisted coil spring (9).
しかしながら、直来の展開機構は以上のように構成され
ているので、展開中ヒンジビン（４）とねじりコイルバ
ネ（９）との間に不規則（不確定）的な摩擦力が発生し
、この為ねじりコイルバネ（９）のプリトルクの設定が
困難であった。これを解消するにはねじりコイルバネ（
９）の平均半径を大きくしてできるだけヒンジビン（４
）との接触を少なく［２、しかもこの不規則（不確定）
的な摩擦力をあらかじめ考慮してねじりコイルバネ（９
）のプリトルクを設定しなければならなかった。However, since the original deployment mechanism is configured as described above, irregular (indeterminate) frictional force is generated between the hinge pin (4) and the torsion coil spring (9) during deployment. It was difficult to set the pre-torque of the torsion coil spring (9). To solve this problem, use a torsion coil spring (
9) to increase the average radius of the hinge bin (4) as much as possible.
) [2, and this irregularity (uncertain)
A torsion coil spring (9
) had to set the pre-torque.
さらに展開機構を構成した状樟でのねじりコイルバネ（
９）のブＩＪ ）ルクの大巾な調整は困難であり、これ
を実施するにけプリトルクの異なる別のねじりコイルバ
ネを組込まなければならなかった。その上展開機構を構
成する際、組立が複雑であったという欠点があった。Furthermore, the torsion coil spring made of camphor that constituted the deployment mechanism (
9) It is difficult to adjust the torque over a wide range, and in order to do this, it was necessary to incorporate another torsion coil spring with a different pretorque. Furthermore, there was a drawback in that the assembly of the unfolding mechanism was complicated.
この発明は上記の欠点を解消するためになされたもので
、ヒンジの一方のクレビス金Ａと一体であるヒンジビン
の軸端に渦巻きバネを巻き付は、他方のクレビス金具に
スリーブ及びスリーブ固定ネジを介して前記渦巻きバネ
の端部を固定することにより、太陽電池パドルを展開し
、展開中のヒンジビンと渦巻きバネとの摩擦力を解消し
、渦巻きバネのプリトルクの大巾な１Ｉｌｖ整ができ、
さらに展開機構の組立が簡単である太陽電池パドルの展
開機構を提供するものである。This invention was made to solve the above-mentioned drawbacks.A spiral spring is wound around the shaft end of the hinge pin that is integrated with the clevis fitting A on one side of the hinge, and a sleeve and sleeve fixing screw are attached to the other clevis fitting. By fixing the end of the spiral spring through the solar cell paddle, the solar battery paddle is deployed, the frictional force between the hinge bin and the spiral spring during deployment is eliminated, and the pre-torque of the spiral spring can be adjusted to a wide range of 1Ilv,
Furthermore, the present invention provides a solar battery paddle deployment mechanism that is easy to assemble.
以下この発明の一実施例を図について説明する。An embodiment of the present invention will be described below with reference to the drawings.
第４図、第５図に示すように、パネル（１） ｆ２＋に
取付けられたクレビス金具（３１（６＋をヒンジビン（
４）とベアリング０υとを介して、回転自在な連結状襲
とするいわゆるヒンジ構造は同様であるが、この実施例
では、クレビス金具（３）と一体であるヒンジビン（４
）の軸端に渦巻きバネ（５）を巻きつけて他方のクレビ
ス金具ｆ６１ Ｋスリーブ（７）及びスリーブ固定ネジ
（８）を介して前記渦巻きバネ（５）の端部を固定して
いる。As shown in Figures 4 and 5, the clevis fitting (31 (6+) attached to the panel (1) f2+ is attached to the hinge bin (
4) and a bearing 0υ, the so-called hinge structure is the same, but in this embodiment, the hinge pin (4) is integrated with the clevis fitting (3).
) is wound around the shaft end of the spiral spring (5), and the end of the spiral spring (5) is fixed via the other clevis fitting f61 K sleeve (7) and the sleeve fixing screw (8).
次Ｖこ動作について説明するり
第６図ではパネル（１）（２）が格納された状態金示し
ているが、太陽電池パドルの保持解放機構（図示せず）
が解放されれば、ヒンジビン（４）の軸端に巻き付けら
れ、端部がスリーブ（力及びスリーブ固定ネジ（８）を
介して他方のクレビス金具（６）に固定されている渦巻
きバネ（５）の回転トルクにより確実にパネル（１１＋
２）を展開する。Next, we will explain the operation of the solar panel. Figure 6 shows the panels (1) and (2) in the retracted state, but the solar battery paddle holding and releasing mechanism (not shown) is shown in Figure 6.
is released, the spiral spring (5) is wound around the shaft end of the hinge bin (4) and the end is fixed to the other clevis fitting (6) via the sleeve (force and sleeve fixing screw (8)). The rotating torque ensures that the panel (11+
Expand 2).
第４図、第８図に示すような構造であるために、ヒンジ
部のみの組立ができ、ユニット化が実施できる。それに
展開中におけるヒンジビン（４）と渦巻きバネ（５）の
摩擦が全く解消されたために、この分の渦巻きバネのプ
ＩＪ ）ルクが小さくでき、ヒンジ部の負荷が小さくな
る。さらに渦巻きバネを異なったプリトルクの渦巻きバ
ネと交換することなく一つの渦巻きバネで、その取付角
度を変えてやることにより、渦巻きバネ（５）のブＩＪ
）ルクが大巾に調整できる。Since the structure is as shown in FIGS. 4 and 8, only the hinge portion can be assembled and unitization can be implemented. In addition, since the friction between the hinge pin (4) and the spiral spring (5) during deployment is completely eliminated, the torque of the spiral spring can be reduced accordingly, and the load on the hinge portion can be reduced. Furthermore, by changing the mounting angle of a single spiral spring without replacing the spiral spring with a spiral spring of a different pre-torque, the spiral spring (5) can be
) Lux can be adjusted to a wide width.
（第８図において９０°ごとに渦巻きバネのプリトルク
が調整できる）
以上のように、この発明によれば、一方のクレビス金具
と一体であるヒンジビンの軸端に渦巻きバネを巻き付け
て、端部をスリーブ及びスリーブ固定ネジを介して他方
のクレビス金具に固定することにより、展開機構の組立
が簡単でしかもヒンジ部のユニット化ができ展開中のヒ
ンジビンと渦巻きバネの摩擦の解消、さらに渦巻きバネ
のブＩＪ トルクが取付角変を変えてやることにより大
巾な調整ができるという利漬がある。(In Fig. 8, the pre-torque of the spiral spring can be adjusted in 90° increments.) As described above, according to the present invention, the spiral spring is wound around the shaft end of the hinge bin that is integrated with one of the clevis fittings, and the end portion is By fixing the sleeve to the other clevis fitting via the sleeve and the sleeve fixing screw, assembly of the deployment mechanism is easy, and the hinge part can be made into a unit, eliminating friction between the hinge pin and the spiral spring during deployment, and further preventing the spiral spring from closing. There is an advantage that IJ torque can be adjusted over a wide range by changing the mounting angle.
第１図〜第３図は、従来の展開型太陽電池パドルの展開
機構を示す図で、第１図、第２図は展開完了後の平面図
及び正面図、第３図は太陽電池パドル格納状態の正面図
１１第４図〜第８図はこの発明の−￥施例を示す図で、
第４図、第５図は展開完了後の平面図及び正α１１図、
第６図１ま太陽電池パドル格納状性の正面図、第７図は
展開中の「１−面図、第８図Ｖｉ渦巻きバネの取付方法
をホす正面図であるワ
図中（１１ｆ２＋はパネル、（３１＋６１ ）まクレビ
ス金具、（４）ｔユヒンジピン、＋５１ｆｌ渦巻きバネ
、（７）はスリーブ、（８）ｔまスリーブ固定ネジ、ａ
ｕｒ、ｘベアリングである。
なお図中同一あるいは相当部分には同−杓号を付して示
しである。
代理人 葛 野 イｇ −Figures 1 to 3 are diagrams showing the deployment mechanism of a conventional deployable solar battery paddle. Figures 1 and 2 are a plan view and a front view after deployment is completed, and Figure 3 is a solar battery paddle storage. Front view of state 11 Figures 4 to 8 are views showing -\ embodiments of this invention.
Figures 4 and 5 are the plan view and normal α11 view after the development is completed,
Fig. 6 is a front view of the solar battery paddle retracted state, Fig. 7 is a 1-side view during development, and Fig. 8 is a front view showing how to install the spiral spring (11f2+ is Panel, (31+61) clevis fitting, (4) t hinge pin, +51fl spiral spring, (7) sleeve, (8) t sleeve fixing screw, a
ur, x bearing. Note that the same or equivalent parts in the figures are indicated with the same symbol. Agent Ig Kuzuno -
Claims (1)
ビス金具と一体となったヒンジビンの軸端に渦巻きバネ
を巻き付け、他方のクレビス金具にはスリーブ及びスリ
ーブ固定ネジを介して、前記渦巻きバネの端部を固定し
たことを特徴とする展開型太陽電池パドルの展開機構。A spiral spring is wound around the shaft end of a hinge bin that is integrated with one clevis fitting of a hinge that connects a plurality of solar cell panels, and the end of the spiral spring is wrapped around the other clevis fitting via a sleeve and a sleeve fixing screw. A deployment mechanism for a deployable solar battery paddle characterized by a fixed portion.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE3215431A DE3215431C2 (en) | 1982-04-24 | 1982-04-24 | Device for deploying solar generators |
| DE3215431.3 | 1982-04-24 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS58188800A true JPS58188800A (en) | 1983-11-04 |
| JPH0471760B2 JPH0471760B2 (en) | 1992-11-16 |
Family
ID=6161917
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP58056784A Granted JPS58188800A (en) | 1982-04-24 | 1983-03-31 | Unfolding mechanism of unfolding type solar cell paddle |
Country Status (2)
| Country | Link |
|---|---|
| JP (1) | JPS58188800A (en) |
| DE (1) | DE3215431C2 (en) |
Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| IT1222756B (en) * | 1987-09-29 | 1990-09-12 | Contraves Italiana Spa | FLAT ARTICULATION MECHANISM WITH DIRECT AND REVERSE MOTION WITHOUT ELECTRIC MOTION ACTUATORS, FOR SPATIAL APPLICATIONS |
| DE4032112A1 (en) * | 1990-10-10 | 1992-04-16 | Marcus Metzger | Locking mechanism for deployed satellite solar generator - has spring assisting original deployment of solar panels and providing rigidity in locking position |
| US5509747A (en) * | 1992-10-24 | 1996-04-23 | Deutsche Aerospace Ag | Articulation arrangement for connecting folding structure elements |
| US5673459A (en) * | 1994-09-28 | 1997-10-07 | Space Systems/Loral, Inc. | Deployment hinge apparatus |
| DE19610297C1 (en) * | 1996-03-15 | 1997-01-23 | Daimler Benz Aerospace Ag | Satellite solar generator panel deployment device |
| JP2001039400A (en) | 1999-06-17 | 2001-02-13 | Daimlerchrysler Ag | Expansion joint for satellite sunlight generator |
| DE102011114473B3 (en) * | 2011-09-28 | 2013-01-31 | Astrium Gmbh | Joint for deploying and locking a solar generator or a reflector |
| DE102021102980A1 (en) | 2021-02-09 | 2022-08-11 | Deployables Cubed GmbH | Boom system for a satellite |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2371343A1 (en) * | 1976-11-17 | 1978-06-16 | Aerospatiale | DEVICE FOR THE SYNCHRONIZED DEPLOYMENT OF ARTICULATED ELEMENTS CARRYING SOLAR CELLS IN A PANEL SHAPED BY A SUCCESSION OF SUCH ELEMENTS |
-
1982
- 1982-04-24 DE DE3215431A patent/DE3215431C2/en not_active Expired
-
1983
- 1983-03-31 JP JP58056784A patent/JPS58188800A/en active Granted
Also Published As
| Publication number | Publication date |
|---|---|
| DE3215431C2 (en) | 1985-11-07 |
| JPH0471760B2 (en) | 1992-11-16 |
| DE3215431A1 (en) | 1983-10-27 |
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