JPH0471760B2 - - Google Patents
Info
- Publication number
- JPH0471760B2 JPH0471760B2 JP58056784A JP5678483A JPH0471760B2 JP H0471760 B2 JPH0471760 B2 JP H0471760B2 JP 58056784 A JP58056784 A JP 58056784A JP 5678483 A JP5678483 A JP 5678483A JP H0471760 B2 JPH0471760 B2 JP H0471760B2
- Authority
- JP
- Japan
- Prior art keywords
- spiral spring
- hinge pin
- sleeve
- hinge
- solar battery
- 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 - Lifetime
Links
- 230000001788 irregular Effects 0.000 description 2
- 241000723221 Crepis Species 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000004804 winding Methods 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)
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、第１図〜第
３図に示すようなものがあつた。図において、
１，２はその表面に太陽電池セル（図示せず）が
貼られたパネル、３はパネル１のコーナー部に取
付けられたクレビス金具、４は前記クレピス金具
３と一体であるヒンジピン、６は前記パネル２の
コーナー部に取付けられたクレビス金具、９は前
記ヒンジピン４に巻き付けられたねじりコイルバ
ネ、１０は前記ねじりコイルバネ９の端部保持
具、１１は前記クレビス金具６と一体となつたベ
アリングであつて、前記ヒンジピン４とベアリン
グ１１の回転自在な連結により、両パネル１，２
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つている。 Conventionally, this type of unfolding mechanism has been as shown in FIGS. 1 to 3. In the figure,
1 and 2 are panels with solar cells (not shown) pasted on their surfaces; 3 is a clevis fitting attached to the corner of the panel 1; 4 is a hinge pin integral with the crepis fitting 3; and 6 is the clevis fitting 3. A clevis fitting is attached to a corner of the panel 2, 9 is a torsion coil spring wound around the hinge pin 4, 10 is an end holder for the torsion coil spring 9, and 11 is a bearing integrated with the clevis fitting 6. Through the rotatable connection between the hinge pin 4 and the bearing 11, both panels 1 and 2 are connected.
It is designed to be folded before use and unfolded when used.
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 FIG. 3, when the holding and releasing mechanism (not shown) of the solar array paddle is released from the folded state before use, the torsion that is wrapped around the hinge pin 4 that is integrated with the clevis fitting 3 on one side of the hinge is released. The solar battery paddle is expanded by the rotational torque of the coil spring 9.
しかしながら、従来の展開機構は以上のように
構成されているので、展開中ヒンジピン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つた。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
きるだけヒンジピン４との接触を少なくし、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つた。さらに展開機構を構成
した状態でのねじりコイルバネ９のプリトルクの
大巾な調整は困難であり、これを実施するにはプ
リトルクの異なる別のねじりコイルバネを組込ま
なければならなかつた。その上展開機構を構成す
る際、組立が複雑であつたという欠点があつた。 However, since the conventional deployment mechanism is configured as described above, an irregular (indeterminate) frictional force is generated between the hinge pin 4 and the torsion coil spring 9 during deployment, resulting in a pre-torque of the torsion coil spring 9. The settings were difficult. To solve this problem, the average radius of the torsion coil spring 9 is increased to minimize contact with the hinge pin 4, and the pre-torque of the torsion coil spring 9 is set in consideration of this irregular (uncertain) frictional force in advance. I had to. Further, it is difficult to widely adjust the pre-torque of the torsion coil spring 9 in the state in which the deployment mechanism is configured, and in order to do this, it is necessary to incorporate another torsion coil spring with a different pre-torque. Furthermore, there was a drawback that the assembly was complicated when configuring the unfolding mechanism.
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具と一体で
あるヒンジピ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
ンジピ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調整ができ、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, and involves winding a spiral spring around the shaft end of a hinge pin that is integrated with one clevis fitting of the hinge.
By fixing the end of the spiral spring to the other clevis fitting via the sleeve and sleeve fixing screw, the solar array paddle is deployed, the frictional force between the hinge pin and the spiral spring during deployment is eliminated, and the spiral spring is To provide a solar battery paddle deployment mechanism that allows pre-torque adjustment over a wide range and allows easy assembly of the deployment mechanism.
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１，２に
取付けられたクレビス金具３，６をヒンジピン４
とベアリング１１とを介して、回転自在な連結状
態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
ジピン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６にスリーブ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 FIGS. 4 and 5, attach the clevis fittings 3 and 6 attached to the panels 1 and 2 to the hinge pin 4.
The so-called hinge structure is similar in that the hinge pin 4 is rotatably connected via the clevis fitting 3 and the bearing 11, but in this embodiment, the spiral spring 5 is wound around the shaft end of the hinge pin 4 which is integral with the clevis fitting 3, and the other The end of the spiral spring 5 is fixed to the clevis fitting 6 via a sleeve 7 and a sleeve fixing screw 8.
次に動作について説明する。 Next, the operation will be explained.
第６図ではパネル１，２が格納された状態を示
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、ヒンジピン４の軸端に
巻き付けられ、端部がスリーブ７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１，２を展開する。 Although the panels 1 and 2 are shown in a retracted state in FIG. 6, when the holding and releasing mechanism (not shown) of the solar array paddle is released, the panels are wrapped around the shaft end of the hinge pin 4, and the end becomes a sleeve. The panels 1 and 2 are reliably expanded by the rotational torque of the spiral spring 5 which is fixed to the other clevis fitting 6 via the sleeve fixing screw 7 and the sleeve fixing screw 8.
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、ユツト化が実施
できる。それに展開中におけるヒンジピン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リトルクが小さくでき、ヒン
ジ部の負荷が小さくなる。さらに渦巻きバネを異
なつ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のプリトルクが大巾
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 it can be made into a unit. In addition, since the friction between the hinge pin 4 and the spiral spring 5 during deployment is completely eliminated, the pre-torque of the spiral spring can be reduced accordingly, and the load on the hinge portion can be reduced. Furthermore, the pretorque of the spiral spring 5 can be adjusted over a wide range by changing the mounting angle of one spiral spring without replacing the spiral spring with a spiral spring of a different pretorque.
（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ピンの軸端に渦巻き
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
ジ部のユニツト化ができ展開中のヒンジピンと渦
巻きバネの摩擦の解消、さらに渦巻きバネのプリ
トルクが取付角度を変えてやることにより大巾な
調整ができるという利点がある。 (In Fig. 8, the pretorque 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 pin that is integrated with one of the clevis fittings, and the end portion is By fixing 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 reducing the pre-torque of the spiral spring. It has the advantage that wide adjustments can be made 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、第４図〜第８図はこの発
明の一実施例を示す図で、第４図、第５図は展開
完了後の平面図及び正面図、第６図は太陽電池パ
ドル格納状態の正面図、第７図は展開中の正面
図、第８図は渦巻きバネの取付方法を示す正面図
である。
図中１，２はパネル、３，６はクレビス金具、
４はヒンジピン、５は渦巻きバネ、７はスリー
ブ、８はスリーブ固定ネジ、１１はベアリングで
ある。なお図中同一あるいは相当部分には同一符
号を付して示してある。
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 front view after deployment is completed, and Figure 3 is a solar battery paddle storage. 4 to 8 are views showing one embodiment of the present invention; FIGS. 4 and 5 are a plan view and a front view after deployment is completed; and FIG. 6 is a solar battery paddle storage state. FIG. 7 is a front view of the device in its expanded state, and FIG. 8 is a front view showing how to attach the spiral spring. In the figure, 1 and 2 are panels, 3 and 6 are clevis fittings,
4 is a hinge pin, 5 is a spiral spring, 7 is a sleeve, 8 is a sleeve fixing screw, and 11 is a bearing. Note that the same or corresponding parts in the figures are indicated by the same reference numerals.
Claims (1)
一方のクレビス金具と一体となつたヒンジピンの
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。1. Wrap a spiral spring around the shaft end of a hinge pin that is integrated with one clevis fitting of a hinge that connects multiple solar battery panels, and attach a spiral spring to the other clevis fitting via a sleeve and a sleeve fixing screw.
A deployment mechanism for a deployable solar battery paddle, characterized in that an end portion of the spiral spring is fixed.
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 JPS58188800A (en) | 1983-11-04 |
| JPH0471760B2 true 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 |
|---|---|
| DE3215431A1 (en) | 1983-10-27 |
| JPS58188800A (en) | 1983-11-04 |
| DE3215431C2 (en) | 1985-11-07 |
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