JPH04126700A - Holding/releasing apparatus - Google Patents
Holding/releasing apparatusInfo
- Publication number
- JPH04126700A JPH04126700A JP2248397A JP24839790A JPH04126700A JP H04126700 A JPH04126700 A JP H04126700A JP 2248397 A JP2248397 A JP 2248397A JP 24839790 A JP24839790 A JP 24839790A JP H04126700 A JPH04126700 A JP H04126700A
- Authority
- JP
- Japan
- Prior art keywords
- pin
- panel
- holding
- holding pin
- coil spring
- 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
- 230000006835 compression Effects 0.000 claims abstract description 12
- 238000007906 compression Methods 0.000 claims abstract description 12
- 239000002184 metal Substances 0.000 claims description 5
- 230000000694 effects Effects 0.000 abstract description 5
- 238000004880 explosion Methods 0.000 abstract 1
- 235000006508 Nelumbo nucifera Nutrition 0.000 description 1
- 240000002853 Nelumbo nucifera Species 0.000 description 1
- 235000006510 Nelumbo pentapetala Nutrition 0.000 description 1
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- Photovoltaic Devices (AREA)
Abstract
Description
【発明の詳細な説明】
し産業上の利用分野］
この発明は１例えば人工衛星に搭載され、かつその表面
に太陽電池が貼られた複数枚のパネルで構成される展開
型太陽電池パネルにおいて、パネル展開時にパネルの拘
束を解放する装置に関するものである。[Detailed Description of the Invention] Industrial Application Field] The present invention relates to a deployable solar cell panel that is mounted on, for example, an artificial satellite and is composed of a plurality of panels with solar cells pasted on the surface thereof. This invention relates to a device that releases the restraint of a panel when it is unfolded.
［従来の技術］
従来、この種装置として第４図に示すものがあった。第
４図はパネル保持状態を示すもので１図において（１）
は、太陽電池（２）が貼られた複数枚のパネル、（３）
は衛星側壁、（４）はパネル（１）同士あるいは衛星側
壁（３）と、これに一番近いパネルを結合し、展開させ
る蝶番、（５）はパネル（１）に埋込まれたブノノユ、
（６）はブノンユ（５）を貫通するピン。[Prior Art] Conventionally, there has been a device of this type as shown in FIG. Figure 4 shows the panel holding state, and in Figure 1 (1)
consists of multiple panels with solar cells (2) attached, (3)
is the satellite side wall, (4) is the hinge that connects the panels (1) or the satellite side wall (3) and the panel closest to this and expands it, (5) is the bunonoyu embedded in the panel (1),
(6) is a pin that passes through Bunonyu (5).
（７）は衛星側壁（３）に取付けられたブラケット、（
８）はブラケット（７）に組み込まれピン（６）を拘束
するロッド、（９）はブラケット（７）とロッド（８）
の隙間に組み込まれた圧縮コイルバネである。また、
（１０）はピン（６）を締込むためのナツト、 （Ｉ
Ｉ）は圧縮コイルバネ、 （１２）は圧縮コイルバネ
（］ｌ）のガイドとなるケース、（１，３）はケース（
１２）をピン（６）に固定するためのナツトである。(7) is a bracket attached to the satellite side wall (3), (
8) is a rod that is incorporated into the bracket (7) and restrains the pin (6), and (9) is the bracket (7) and rod (8).
It is a compression coil spring built into the gap between. Also,
(10) is a nut for tightening the pin (6), (I
I) is a compression coil spring, (12) is a case that serves as a guide for the compression coil spring (]l), and (1, 3) is a case (
12) to the pin (6).
従来の保持解放装置は一４二記のように構成され。A conventional holding and releasing device is constructed as shown in No. 142.
衛星打上時においては、第４図に示すように複数枚のパ
ネル（１）は衛星側壁（３）Ｌに格納された状醤となっ
ている。すなわち２ブ、ン、（５）を貫通するピン（６
）は、その下端部の凹部りにロッド（８）が力Ｆにより
押付けられ、はまり込むことにより拘束され、一方ピン
（６）の上部ではす７ト（ＩＱ）で締付ける。二とによ
り、ブ、ツユ（５）ひいてはパネル（＋）を衛星側壁（
３）１−に、力Ｐで押付は拘束している。When the satellite is launched, the plurality of panels (1) are housed in the satellite side wall (3)L, as shown in FIG. In other words, the pin (6) that passes through the two pins (5)
) is restrained by the rod (8) being pressed by a force F into the recessed part at its lower end and being fitted, while the rod (8) is tightened at the upper part of the pin (6) with an inlet (IQ). 2, the panel (+) is attached to the satellite side wall (
3) In 1-, pressing is restrained by force P.
軌道ヒにおいて、パネル（１）を展開するために爆管装
置！等（図示せず）で、力Ｆを解放すると７第５図に示
すように、ロンド（８）が圧縮コイルバネ（９）のバ不
力により、ブラケット（７）の中を矢印（イ）方向に摺
動しピン（６）の拘束を解（、解放されたピン（６）は
圧縮フィルバネ（ＩＩ）のバ不力によりブツシュ（５）
間を一気に引抜かれ、第６図に示すように圧縮コイルバ
ネ（１１）の残留バネ力により外端パネルのブツシュに
保持され、パネル（１）の展開が開始されるのである。In orbit, a detonator device is used to deploy panel (1)! (not shown), when the force F is released, the rond (8) moves in the direction of the arrow (A) inside the bracket (7) due to the tension of the compression coil spring (9), as shown in Figure 5. The restraint of the pin (6) is released (the released pin (6) is pressed against the bush (5) by the force of the compressed fill spring (II).
As shown in FIG. 6, the panel (1) is held by the bushing of the outer end panel by the residual spring force of the compression coil spring (11), and the panel (1) begins to unfold.
［発明が解決しようとする課題］
上記の様な従来の保持解放装置においては、パネル格納
状態において、ピン（６）の凹部りにより力Ｐてロッド
（８）の端部を第４図矢印（Ａ＞の方向ｌこ引張ってい
ることになる。衛星打上時の四ケノト・の振動等を考慮
するとパネル（１）を衛星側壁（３） ニ１７つかつと
固定するために力Ｐを大きくとる必要があるが、解放装
置（爆管）が作動して力Ｆが解放されても、上述したよ
うにロンド（８）の端部が矢印（Ａ）の方向に力を受け
てブラケット（７）の中を摺動せずパネル（］）の解放
に至らない場合があるという課題があった。[Problems to be Solved by the Invention] In the conventional holding and releasing device as described above, when the panel is in the retracted state, the end of the rod (8) is moved by the force P by the recessed portion of the pin (6) in the direction shown by the arrow in FIG. This means that the panel is being pulled in the direction of A. Considering the vibrations caused by the satellite during launch, a large force P is required to secure the panel (1) to the satellite side wall (3). However, even if the release device (detonator) is activated and the force F is released, the end of the rondo (8) receives force in the direction of the arrow (A) as described above, and the bracket (7) There was a problem in that there were cases where the panel (]) could not be released because it did not slide inside the panel.
この発明はかかる課題を解決するためになされたもので
、パネル展開時に確実にパネルが解放できる信頼性の高
い保持解放装置を得ることを目的とする。The present invention was made to solve this problem, and an object of the present invention is to obtain a highly reliable holding and releasing device that can reliably release a panel when it is unfolded.
１課題を解決するための手段］
この発明に係る保持解放装置は、保持ピンの先端を球形
状とし、この先端部をてこの−ｉて押さえることができ
るように、そ３及び：Ｃ３の回転中心となるピンを、衛
星側壁に固定されたブラケット内に配置し、このてこの
他端にワイヤローブ及び引張コイルバネを、てこを中心
にして互いに引張り合うように一直線状に配置したもの
である。[Means for Solving Problem 1] The holding and releasing device according to the present invention has a spherical tip end of the holding pin, and the rotation of part 3 and :C3 is such that the tip part can be held down with a lever. A central pin is placed in a bracket fixed to the side wall of the satellite, and a wire lobe and a tension coil spring are placed at the other end of the lever in a straight line so as to pull each other around the lever.
「作用；
この発明においては、解放装置（爆管）作動後、保持ピ
ンが確実に解放され、パネル展開が失敗な〈実施できる
ようにしたものである。``Function: In this invention, after the release device (detonator) is activated, the holding pin is reliably released, so that the panel expansion can be carried out without failure.
゛一実施例１
第１図〜第３図はこの発明の一失゛施例を示す断面図で
あり、（１）〜（５）までは従来装置と同一のちのであ
る。 （１４）はブ、シコ（５）内を貫通し球形状の先
端部を何する保持ピン、 （１，５）はす、ト（ＩＱ
）と前記保持ピン（１４）の間に組み込まれた圧縮コイ
ルハネ、 （＋６）は衛星側壁（３）上に取付けられた
ブラケット、（＋７）はピン（）８）を回転中心とする
てこ、（１９）は前記ブラケノ）（１６）の上部に組み
込まねたブツシュ、 （２０）は前記てこ（１７）の下
端部に組み込まれたピン（２１）に対し回転自在な金具
、 （２２）は前記金具（２０）の端部に固定されたケ
ーブル、 （２３）は前記ピン（２１）に端部を引掛ζ
すて組み込んだ引張コイルバネ、 （２４）は前証ブラ
ケ／ト（１６）に固定され、前記引張フィルバネ（２３
）の他端を固定しているピン（２５）は前記ブラケット
（１６）に固定されたストッパ（２６）は前記ケース（
１２）を、前記ブノンユ（５）に固定するためのネジで
ある。Embodiment 1 FIGS. 1 to 3 are sectional views showing one embodiment of the present invention, and (1) to (5) are the same as the conventional device. (14) is a holding pin that passes through the inside of the rod (5) and has a spherical tip.
) and the holding pin (14), (+6) is a bracket attached to the satellite side wall (3), (+7) is a lever with the pin ()8) as the center of rotation, ( 19) is a bushing installed in the upper part of the bracket (16), (20) is a metal fitting that is rotatable with respect to the pin (21) installed in the lower end of the lever (17), and (22) is the metal fitting. The cable (23) is fixed to the end of (20), and the end of (23) is hooked to the pin (21).
The tension coil spring (24) installed in the front is fixed to the front bracket (16), and the tension fill spring (23)
) is fixed to the other end of the pin (25), and the stopper (26) fixed to the bracket (16) is fixed to the case (
12) to the bunonyu (5).
上記のように構成された保持解放装置においては、衛星
打り時に第１図に示すように複数枚のパネル（１）は衛
星側壁（３）十に格納された状態となっている。すなわ
ちブ、ンユ（５）及び（１９）を貫通する保持ピン（１
４）は、その下端部の球形状部Ｑにおいて、てこ（１７
）の上端部Ｔで押付けて拘束され（その時の押付力はケ
ーブル（２２）を引張る力Ｆにより発生する。）、一方
ｍｌ記保持ピン（１４）の上部では、ナソ） （ＩＣ）
により１前記保持ピン（１４）の上部に組み込まれた圧
縮コイルバネ（１５）を、外端パネル（１）に組み込ま
れたブソンー（５）に締付けることで、前記保持ピン（
１４）を力Ｐて引張−トげる方向に力を加え結果的には
、パネル（１）を衛星側壁（３）上に力Ｐで押付けて拘
束している。この時力Ｐは前記保持ピン（１４）上部の
雄ネジ部に噛合う前記すｙト（１０）を回転させること
により調節できる。In the holding and releasing device configured as described above, the plurality of panels (1) are stored in the satellite side wall (3) as shown in FIG. 1 during satellite launch. In other words, the holding pin (1) that passes through the holes (5) and (19)
4) has a lever (17
) is pressed and restrained by the upper end T (the pressing force at that time is generated by the force F that pulls the cable (22)), while the upper part of the retaining pin (14) is pressed and restrained (IC)
1. By tightening the compression coil spring (15) incorporated in the upper part of the retaining pin (14) to the bushon (5) incorporated in the outer end panel (1), the retaining pin (14) is tightened.
14) in a pulling direction with a force P, and as a result, the panel (1) is pressed onto the satellite side wall (3) with a force P and restrained. At this time, the force P can be adjusted by rotating the shaft (10) that engages with the male threaded portion on the upper part of the holding pin (14).
次に動作について説明する。軌道上において１、パネル
（１）を解放するために爆管装置等（図示せず）で力Ｆ
を解放すると、前記保持ピン（Ｉ４）に加えられていた
力Ｐと、引張コイルバネ（２３）の力により、てこ（１
７）がピン（１８）を中心としてＢの方向に回転し、前
記保持ピン〈Ｉ４）の拘束か解放される第２図に示すよ
うに解放された前記保持ピン（１イ）は、前記圧縮コイ
ルバネ（１５）により、パネル格納状態よりも北方に動
くが、ケース（１２）によって移動範囲は拘束される。Next, the operation will be explained. 1. In orbit, a force F is applied using a detonator device (not shown) to release the panel (1).
When the lever (1) is released, the force P applied to the holding pin (I4) and the force of the tension coil spring (23)
7) rotates in the direction of B around the pin (18), and the holding pin (I4) is released from the restraint.As shown in FIG. The coil spring (15) moves the panel further north than in the retracted state, but the range of movement is restricted by the case (12).
一方、拘束が解放されたパネル（１）は蝶番（４）を回
転中心として各々展開するが、前記保持ピン（１４）が
、前記衛？側壁（３）に近い方のプノンユ（５）から順
次抜けて行く。パネル（１）の展開が完全に終了すると
、第３図に示すような形状となり、前記保持ピン（１２
）の外端パネル（１）より突出た部分は太陽電池（２）
が貼られていない側に飛出た状態で保持される。On the other hand, the released panels (1) unfold around the hinges (4) as centers of rotation, but the holding pins (14) do not touch the guard. Pass through in sequence starting with Phnom Yu (5), which is closer to the side wall (3). When the panel (1) is completely expanded, it will have a shape as shown in Figure 3, and the holding pin (12
) The part that protrudes from the outer end panel (1) is the solar cell (2)
It is held in a state where it sticks out to the side where it is not pasted.
第１図において、前記保持ピン（１４）の拘束が解放さ
れる時は、前記てこ（１７）の回転に依存し、摺動に頼
らないため、解放機能の信頼性が高い。In FIG. 1, when the holding pin (14) is released, it depends on the rotation of the lever (17) and does not rely on sliding, so the release function is highly reliable.
また第３図において、前記ケース（１２）の長さを調整
することにより、太陽電池受光面形が落ちることを防止
できる。Further, in FIG. 3, by adjusting the length of the case (12), it is possible to prevent the solar cell light-receiving surface shape from falling.
［発明の効果］
この発明は１以上説明した通り、保持ピンか確実に解放
できる保持解放装置を提供することにより、太陽電池パ
ネル展開の信頼性を高めるという効果があると共に、太
陽電池受光面に影が落ちることを防止するという効果が
ある。[Effects of the Invention] As explained above, the present invention has the effect of increasing the reliability of solar cell panel deployment by providing a holding and releasing device that can reliably release the holding pins, and also has the effect of increasing the reliability of solar cell panel deployment. This has the effect of preventing shadows from falling.
第１図は、この発明の一実施例を示す太陽電池パネル格
納状態の断面図、第２図は同じく解放装置作動直後の断
面図、第３図も同じ（この発明の一実施例を示す太陽電
池パネル展開後の状態を示す断面図、第４図、第５図、
第６図は従来の保持解放装置を示す断面図で、ＷＩに太
陽電池パネル格納図において、（１）はパネル、（２）
は太陽電池、（３）は衛星側壁、（４）は蝶番、（５）
はブツシュ、（６）は保持ピン、（７）はブラケット、
（８）はロッド、（９）は圧縮コイルバネ、 （１０）
はす、 ｌ−、（１１）は圧縮コイルバネ、（１２）・
はケース、 （１３）はナツト、 （１４）は保持
ピン、 （１５）は圧縮コイルバネ、 （＋６）は
ブラケット、 （１７）はてこ、 （１８）はピン
、 （１９）はブツシュ、 （２（１）は金具。
（２１）はピン、 （２２）はケーブル、 （２：
’ｌ）は引張コイルバネ、 （２４）はピン、 （
２５）はスト、バ、 （２６）Ｉまネジである。
なお、各図中、同−一符号は同一または相当部分を示す
。FIG. 1 is a cross-sectional view of a solar cell panel stored in an embodiment of the present invention, FIG. 2 is a cross-sectional view immediately after the release device is activated, and FIG. Cross-sectional views showing the state after the battery panel is expanded, FIGS. 4 and 5,
Figure 6 is a sectional view showing a conventional holding and releasing device.
is the solar cell, (3) is the satellite side wall, (4) is the hinge, (5)
is a bushing, (6) is a holding pin, (7) is a bracket,
(8) is a rod, (9) is a compression coil spring, (10)
Lotus, l-, (11) is a compression coil spring, (12)
is the case, (13) is the nut, (14) is the holding pin, (15) is the compression coil spring, (+6) is the bracket, (17) is the lever, (18) is the pin, (19) is the bushing, (2( 1) is the metal fitting. (21) is the pin, (22) is the cable, (2:
'l) is a tension coil spring, (24) is a pin, (
25) is a strike, a bar, and (26) an I screw. In each figure, the same reference numerals indicate the same or corresponding parts.
Claims (1)
た複数枚のパネルで構成される展開型パネルの保持解放
装置において、前記各パネルに埋め込まれ、パネル格納
状態にて、前記複数枚のパネルを貫通する穴を有する第
１のブッシュ、前記第１のブッシュ内を貫通する保持ピ
ン、前記保持ピン上部の雄ネジ部に組み込まれたナット
、前記パネルの外端パネルに組み込まれた第１のブッシ
ュと前記ナットにて両端部を拘束され、前記保持ピンの
外周部に組み込まれた圧縮コイルバネ、前記外端パネル
に組み込まれた第１のブッシュに固定されたケース、衛
星側壁に固定されたブラケット、前記ブラケット内に組
み込まれ、前記パネルのうち前記衛星側壁に一番近いパ
ネルに組み込まれた第１のブッシュと接する第２のブッ
シュ、前記ブラケット内に固定された第１のピン、前記
第１のピンを回転中心とするように組み込まれ、前記保
持ピン下端の球形状部と接するように凹型形状の先端部
を有するてこ、前記てこの他端部に組み込まれた第２の
ピン、前記第２のピンに対し回転自在に組み込まれたＵ
字形の金具、前記金具に固定されたケーブル、前記第２
のピンにフックが組み込まれ、前記ブラケットに固定さ
れた、第３のピンに、もう一方のフックが組み込まれた
引張コイルバネ、前記ブラケットに固定され、前記てこ
の回転角度を制限するストッパを具備したことを特徴と
する保持解放装置。In a deployable panel holding and releasing device that is mounted on an artificial satellite and is composed of a plurality of panels with solar cells affixed to their surfaces, the device is embedded in each of the panels, and when the panels are in a retracted state, the plurality of panels are a first bushing having a hole passing through the panel; a holding pin passing through the first bushing; a nut built into the male threaded portion of the upper part of the holding pin; a first bushing built into the outer end panel of the panel; A compression coil spring whose ends are restrained by the bush and the nut, a compression coil spring built into the outer periphery of the holding pin, a case fixed to the first bush built into the outer end panel, and a case fixed to the satellite side wall. a second bushing built into the bracket and in contact with a first bushing built into one of the panels closest to the satellite sidewall; a first pin fixed within the bracket; a lever that is incorporated so that the first pin is the center of rotation and has a concave tip that contacts the spherical portion at the lower end of the holding pin; a second pin that is incorporated in the other end of the lever; U is rotatably built into the second pin
a cable fixed to the metal fitting, the second metal fitting;
A third pin has a hook incorporated therein, a third pin has a hook incorporated therein, a tension coil spring is fixed to the bracket, and a stopper is fixed to the bracket and limits the rotation angle of the lever. A holding and releasing device characterized by:
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2248397A JPH04126700A (en) | 1990-09-18 | 1990-09-18 | Holding/releasing apparatus |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2248397A JPH04126700A (en) | 1990-09-18 | 1990-09-18 | Holding/releasing apparatus |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH04126700A true JPH04126700A (en) | 1992-04-27 |
Family
ID=17177501
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP2248397A Pending JPH04126700A (en) | 1990-09-18 | 1990-09-18 | Holding/releasing apparatus |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH04126700A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002061729A (en) * | 2000-06-29 | 2002-02-28 | Astrium Gmbh | Rectilinear operatoin device, spacecraft having the rectilinear operation device, and developing system of solar generator |
| CN105438504A (en) * | 2015-11-30 | 2016-03-30 | 上海宇航系统工程研究所 | Rope collecting and releasing device for multiple sheaves |
| CN109305391A (en) * | 2018-08-08 | 2019-02-05 | 上海宇航系统工程研究所 | Compress relieving mechanism and its method |
-
1990
- 1990-09-18 JP JP2248397A patent/JPH04126700A/en active Pending
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002061729A (en) * | 2000-06-29 | 2002-02-28 | Astrium Gmbh | Rectilinear operatoin device, spacecraft having the rectilinear operation device, and developing system of solar generator |
| CN105438504A (en) * | 2015-11-30 | 2016-03-30 | 上海宇航系统工程研究所 | Rope collecting and releasing device for multiple sheaves |
| CN109305391A (en) * | 2018-08-08 | 2019-02-05 | 上海宇航系统工程研究所 | Compress relieving mechanism and its method |
| CN109305391B (en) * | 2018-08-08 | 2021-12-21 | 上海宇航系统工程研究所 | Compression release mechanism and method thereof |
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