JPS58188798A - Hold-down mechanism - Google Patents
Hold-down mechanismInfo
- Publication number
- JPS58188798A JPS58188798A JP58056774A JP5677483A JPS58188798A JP S58188798 A JPS58188798 A JP S58188798A JP 58056774 A JP58056774 A JP 58056774A JP 5677483 A JP5677483 A JP 5677483A JP S58188798 A JPS58188798 A JP S58188798A
- Authority
- JP
- Japan
- Prior art keywords
- panel
- hold
- lever
- yoke
- 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
- 230000007246 mechanism Effects 0.000 title claims description 26
- 238000005520 cutting process Methods 0.000 claims description 3
- 125000006850 spacer group Chemical group 0.000 description 4
- 238000010586 diagram Methods 0.000 description 2
- 239000003721 gunpowder Substances 0.000 description 2
- 241000282472 Canis lupus familiaris Species 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000001360 synchronised effect 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
- B64G1/2224—Folding about multiple axes
-
- 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
- B64G1/2228—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 hold-down or release mechanisms
-
- 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)
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１表面に太陽′置部セルが配置されたパネル
を衛星本体に折りたたんだ軟性に保持し、かつ展開時に
保持状幅（ｉｌｌ−解放するホールドダウン機構に関す
るものである。DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a hold-down mechanism that flexibly holds a folded panel on one surface of which a solar cell is placed on a satellite body, and releases the holding width (ill-ill) when deployed. It is.
従来のこの檀ホールドダウン機構としては第１図に示す
ものがあった。図ｙｃおいて表ｒｋｊＫ太陽電池セルが
配置されたパネル（１１，（２１及びヨーク（３）はη
いに展開バネを組み込んだヒンジ（４）で結合されてい
る。ホールドダウン機構は、衛星本体αυに固定された
ブラケット（７）、このブラケット（７）に取り付けら
れたボルトカッタ（６）及びボルト（８）から成ってお
り、上端パネル（２）と一体になったプレート（２）を
固定することしこエリ、展開型太陽電池パネルを保持Ｌ
ｌいる。この状態でパネル間及びパネルと衛星本体との
展開方向の相対変１企は、スペーサ（５１，（６）、
ｏ８により制限されている。A conventional hold-down mechanism for this purpose is shown in FIG. In Figure yc, the panels (11, (21) and yoke (3) on which the solar cells are arranged are
They are connected by a hinge (4) incorporating a deployment spring. The hold-down mechanism consists of a bracket (7) fixed to the satellite main body αυ, a bolt cutter (6) and a bolt (8) attached to this bracket (7), and is integrated with the upper end panel (2). Fix the plate (2) and hold the deployable solar panel L
There is. In this state, the relative change in the deployment direction between the panels and between the panels and the satellite main body is accomplished by using the spacers (51, (6),
Restricted by o8.
次に動作について第２図により説明する。パネルの展開
は、パネルを固定しているボルト（８）を点火信号によ
り火薬等で作動するボルトカッタ（２）で切断すること
に工って竹９゜通冨展開型太陽電池パネルの衛星本体へ
の固定は２グ所以上で行なうので、このホールドグ１ク
ン＋１ｋ１１１１もその数だけ必要になる。Next, the operation will be explained with reference to FIG. The panel is deployed by cutting the bolts (8) fixing the panel with a bolt cutter (2) activated by gunpowder or the like in response to an ignition signal. Since the fixing is done in two or more places, the number of holding dogs 1 kun + 1 k1111 is also required.
ところで従来のホールドダウン機構ハ１以上のように構
成されているので１個々のホールドダウン機構が独立し
ており、複数のボールドタウン機構を用いる場合、その
配置が′＃星本体に合せて比較的任意にできる利点ｔま
あるが、ボルトカッタ等を内戚しているので、構成がり
雑となり、複数のホールドダウン＋１Ｒ偽の動作がかな
らすしも同期しない欠点があった。By the way, since the conventional hold-down mechanism is configured as above, each hold-down mechanism is independent, and when using multiple bold town mechanisms, their arrangement is relatively small according to the main body of the star. Although it has the advantage of being arbitrary, it has the disadvantage that the structure is complicated because it includes bolt cutters and the like, and that multiple hold-downs + 1R false operations are not synchronized.
この発明は、これらの従来の欠点を随〈ためになされた
もので、（の特徴とするとこ／）ｒまパネルの衛星本体
への固定は構成の単純なレバー走用い、保持及び解散の
だめのカを発生する機構をホールドダウン機構とは独立
して別個なものとｊ〜、ホールドダウン機構そのも（１
）を即純化し２にことにある。The present invention has been made to overcome these conventional drawbacks, and is characterized by: The fixing of the r panel to the satellite body is a simple lever operation, holding, and disassembly. The mechanism that generates the force is independent and separate from the hold-down mechanism, and the hold-down mechanism itself (1
) can be immediately purified to 2.
以下この発明の一実施例を図によって説明する。第８図
において表面に太陽電池セルを配置し７たパネル（１１
，（２１とヨーク（３）及び律、ｗ′＋体Ｑｌｌとｔま
、互いｆ展開スゲ１１ングを組み込んたヒンジ（４）ｒ
こより結合をれている。この状態でのパネル聞及びパネ
ルと偉ｒ星本体との展開力向の相対変位ｔゴ、スペーサ
（５）、 （６１及びブフヶソＨ７）＆（Ｔよって制限
さ７１ている。この発明の対象となるボールドタウン機
構は、偉■足本体ａＸに固定したブラケット（７１，こ
れに対し、て回転するレバー（８）、スゲリンダ（９）
から構成さねでおり、パネルの格納状輻を維持するため
のカド１を発生きせるため、レバー（８）をワイヤαａ
によりド２の力で弓し辰っている。スプリング（９１Ｈ
１？：ｌ’（ｒ Ｆ ３の力をブラケット（７）トレハ
−ｔｓ＋間に作用し７−ｃ（＾るが、レバー（８）の回
転１１１寸わりに発生するモーメントｒｉ Ｆ ２によ
るものがＦ３によるものより大きいため。An embodiment of the present invention will be described below with reference to the drawings. Figure 8 shows a panel (11) with solar cells arranged on its surface.
, (21 and yoke (3) and Ritsu, w' + body Qll and t, hinge (4) r incorporating f expansion Suge 11 ring
It is more connected than this. In this state, the relative displacement between the panel and the main body of the star in the direction of the development force is limited by the spacer (5), (61 and Bufkaso H7) & (T. The Bold Town mechanism consists of a bracket (71) fixed to the main body aX, a lever (8) that rotates, and a Sgelinda (9).
The lever (8) is connected to the wire αa in order to generate the corner 1 for maintaining the retracted state of the panel.
This allows him to bow with the power of C2. Spring (91H
1? :l'(r F 3's force is applied between the bracket (7) and ts + 7-c (^), but the moment ri F 2 generated by 111 inches of rotation of the lever (8) is due to F3 Because it's bigger.
その差によりパネルの保持に必要な力Ｆｌが発生する。The difference generates the force Fl necessary to hold the panel.
次にパネル展開のための解放動作について説明する。第
３図において、ワイヤ（イ）に作用する力Ｆ２を零近く
にすると、スプリング（９）の力Ｆ３によりレバー（８
）はブラケット（カの軸まわりを図で時計方向に回転す
る。このよう圧してレバ〜（８）がパネル（２）と一体
になったスペーサ（６）から１まずれて、パネルは展開
に対して自由となる。この状態を第４図に示す。Next, the release operation for panel expansion will be explained. In Fig. 3, when the force F2 acting on the wire (A) is made close to zero, the force F3 of the spring (9) causes the lever (8
) is rotated clockwise around the axis of the bracket (as shown in the figure).By pressing in this way, the lever (8) is moved away from the spacer (6) integrated with the panel (2), and the panel is unfolded. This state is shown in FIG.
第５図は、このホールドダウン機構の使用ＮＪである。FIG. 5 shows the use of this hold-down mechanism.
パネル、ヨーク、ヒンジ等で構成ネれ付活Ｑ・で代表さ
れる展開型太陽電池パネルそれぞれ付活（ハ）で代表さ
れる４個のボールドタ功ン機構で衛星本体αυに固定さ
れている。これらのホールドタ′ウン機ｗ４はループ状
をなしたワイヤ（２）及びカットワイヤ（財）ｒｃより
互いに連結して張力Ｆ２を与えられている。今カットワ
イヤ（財）を火薬等で作動するワイヤカッタＱｌこより
切断するとＦ２１ま零ＶＣ近くなり＋ ｓｉｒ述の動作
原理により４個のホールドターラン機構が同時に動作し
で、展開型太陽′電池パネルを解放することができる。The deployable solar cell panel, which is composed of panels, yokes, hinges, etc., is fixed to the satellite main body αυ by four ball joint mechanisms, each represented by a hinge (C). These hold town machines w4 are connected to each other by loop-shaped wires (2) and cut wires rc, and are given tension F2. If you cut the cut wire (Foundation) from the wire cutter Ql operated by gunpowder etc., the F21 will be close to zero VC + According to the operating principle described by Sir, the four hold tarran mechanisms will operate simultaneously to release the deployable solar battery panel. can do.
なお−以上の説明では２枚のパネル及び１枚のヨークか
ら構成される展開型太陽電池パネルについて説明したが
、このホールドダウン機構の適用ｔ１．パネルの枚数及
びヨークのイー１無に左右されず、同型の形状及び展開
機能を有する展開ノ４す太陽電油パネルの保持解放機構
として共通的に使用できるものである。−また、保持力
を与えるだめのワイヤ張力を発生する機構とは独立のも
のであり、その方式ＰＣよって影響を受けるものでもな
い。Note that although the above explanation has been about a deployable solar cell panel composed of two panels and one yoke, the application of this hold-down mechanism t1. Regardless of the number of panels and the presence or absence of a yoke, this mechanism can be commonly used as a holding and releasing mechanism for solar panels with the same shape and deployment function. - Also, it is independent of the mechanism that generates the wire tension that provides the holding force, and is not influenced by the system PC.
以１−のようにこの発明によｔｌば、構成が簡単ナボー
ルドダウン機構を実現することができ。As described in 1- below, according to the present invention, it is possible to realize a nabold-down mechanism with a simple configuration.
唯一ケ所のワイヤカット動作ＶＣより複数のボールドタ
ウン機構が同時に一１作する保持解放系を構成する要素
となり得る利点がある。There is an advantage that a plurality of bold town mechanisms can serve as elements constituting a holding and releasing system that operates at the same time rather than a single wire cutting operation VC.
第１図及び第２図は従来の展開型太陽電池パネルのホー
ルドダウン機構を説明するための図、第８図−第５図は
にの発明によるホールドダウン機構を説明する丸めの図
であ秒（１）、 （！ｌｔｌパネル、（３）はヨーク、
（４）はヒンジ、 （６）（６）はスペ−？、（７）は
ブラケット、（８）はボルト、（９）はスプリング、Ｑ
Ｑはワイヤ、Ｑ１＋は衛星本体、（２）はホルトカッタ
、（２）はプレート、α４はワイヤカッタ。
（ト）はホールドダウン機構、（至）は展開型太陽電池
パネル、（財）はカットワイヤ、 ０ＳＩｒｉスペーサ
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
しである。
代理人 為 野 信 −Figures 1 and 2 are diagrams for explaining the hold-down mechanism of a conventional expandable solar cell panel, and Figures 8-5 are rounded diagrams for explaining the hold-down mechanism according to the invention of Ni. (1), (!ltl panel, (3) yoke,
(4) is the hinge, (6) (6) is the space? , (7) is the bracket, (8) is the bolt, (9) is the spring, Q
Q is the wire, Q1+ is the satellite body, (2) is the Holt cutter, (2) is the plate, and α4 is the wire cutter. (g) is the hold-down mechanism, (to) is the expandable solar cell panel, (b) is the cut wire, and the 0SIri spacer. In the drawings, the same or corresponding parts are designated by the same reference numerals. Agent Nobu Tameno −
Claims (1)
展開バネを組み込んだヒンジで互いに結合して構成した
展開型太陽電池パネルを。 人工衛星の打上げ時に折りたたんで保持するとともに、
展開時には展開信号によって保持機構を解放するように
構成したホールドダウン機構において、衛星本体に固定
したブラケットに対して回動し、かつ上記パネルおよび
ヨークの折りたたみ時にはこれらを保持するレバーと、
上記レバーの一端側とつながりレバーを一回動方向に回
動させるように作用するバネと、上記バネによる回船方
向と反対の回動方向に上記バネの力に抗して上記レバー
を引っばるワイヤとを有し、上記パネルおよびヨークを
折りたたんでおく時には上記ワイヤーの作用でレバーを
固定してパネルおよびヨークを保持し展開時には上記ワ
イヤーを切断することによりレバＬによるロックを解除
してパネルおよびヨークを展開させるようにしたことを
特徴とするホールドダウン機構。[Claims] A deployable solar cell panel comprising a panel on which solar power cells are arranged and a yoke, which are connected to each other by a hinge incorporating a deployable spring. In addition to being folded and held during the launch of a satellite,
a hold-down mechanism configured to release the holding mechanism in response to a deployment signal when deployed, a lever that rotates relative to a bracket fixed to the satellite body and holds the panel and yoke when folded;
A spring connected to one end of the lever and acting to rotate the lever in one rotation direction, and a spring that pulls the lever in a rotation direction opposite to the rotation direction by the spring against the force of the spring. When the panel and yoke are folded, the lever is fixed by the action of the wire to hold the panel and yoke, and when unfolded, the lock by the lever L is released by cutting the wire and the panel and yoke are folded. A hold-down mechanism characterized by an expandable yoke.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE3215432A DE3215432C2 (en) | 1982-04-24 | 1982-04-24 | Hold-down device for deployable solar generators |
| DE32154321 | 1982-04-24 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS58188798A true JPS58188798A (en) | 1983-11-04 |
Family
ID=6161918
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP58056774A Pending JPS58188798A (en) | 1982-04-24 | 1983-03-31 | Hold-down mechanism |
Country Status (2)
| Country | Link |
|---|---|
| JP (1) | JPS58188798A (en) |
| DE (1) | DE3215432C2 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2015085885A (en) * | 2013-11-01 | 2015-05-07 | 株式会社テクノソルバ | Development structure and spacecraft equipped with the same |
Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2531032A1 (en) * | 1982-07-30 | 1984-02-03 | Aerospatiale | TEMPORARY EFFORT DERIVATION DEVICE FOR HOLDING A DEPLOYABLE APPARATUS FOR A SPACE VEHICLE IN A STORAGE POSITION |
| NL8400362A (en) * | 1984-02-06 | 1985-09-02 | Fokker Bv | DEVICE FOR HOLDING OR RELEASING SOLAR PANELS OF A SPACE VESSEL. |
| US4725025A (en) * | 1986-03-21 | 1988-02-16 | Rca Corporation | Deployment system |
| US5319905A (en) * | 1992-09-28 | 1994-06-14 | Spar Aerospace Limited | Panel array deployment apparatus |
| FR2714358B1 (en) * | 1993-12-24 | 1996-03-15 | Aerospatiale | Device for holding and releasing a structure such as a deployable structure on board a spacecraft. |
| FR2822803B1 (en) * | 2001-03-29 | 2003-08-15 | Cit Alcatel | SOLAR GENERATOR STRUCTURE FOR SATELLITE COMPRISING TIMING BETWEEN PANELS |
| US7040210B2 (en) * | 2003-02-18 | 2006-05-09 | Lockheed Martin Corporation | Apparatus and method for restraining and releasing a control surface |
| US7559505B2 (en) | 2005-12-01 | 2009-07-14 | Lockheed Martin Corporation | Apparatus and method for restraining and deploying an airfoil |
| CN107352052B (en) * | 2017-07-19 | 2020-08-18 | 北京吾天科技有限公司 | Linkage type solar wing unlocking and unfolding mechanism |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2853070C3 (en) * | 1978-12-08 | 1981-10-29 | Messerschmitt-Bölkow-Blohm GmbH, 8000 München | Hold-down system for deployable or unfoldable support elements on spacecraft |
-
1982
- 1982-04-24 DE DE3215432A patent/DE3215432C2/en not_active Expired
-
1983
- 1983-03-31 JP JP58056774A patent/JPS58188798A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2015085885A (en) * | 2013-11-01 | 2015-05-07 | 株式会社テクノソルバ | Development structure and spacecraft equipped with the same |
Also Published As
| Publication number | Publication date |
|---|---|
| DE3215432C2 (en) | 1986-10-30 |
| DE3215432A1 (en) | 1983-10-27 |
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