JPS58214500A - Unfolding structure loaded on artificial satellite - Google Patents
Unfolding structure loaded on artificial satelliteInfo
- Publication number
- JPS58214500A JPS58214500A JP57098902A JP9890282A JPS58214500A JP S58214500 A JPS58214500 A JP S58214500A JP 57098902 A JP57098902 A JP 57098902A JP 9890282 A JP9890282 A JP 9890282A JP S58214500 A JPS58214500 A JP S58214500A
- Authority
- JP
- Japan
- Prior art keywords
- panel
- panels
- spacer
- deployment
- artificial satellite
- 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
Landscapes
- Details Of Aerials (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】
この発明は人工衛星に搭載され、収納時におけるパネル
間の衝突をふせぐようにした展開構造物に関するもので
ある。DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a deployable structure that is mounted on an artificial satellite and is designed to prevent collisions between panels during storage.
従来のこの種展開構造物としては第１図に示すようなも
のがあった。図において（１１はパネル、（２）は展開
ヒンジ、（３）は展開防止装置、（４）はスペーサー、
（５）は人工衛星本体である。A conventional deployable structure of this type is shown in FIG. In the figure (11 is the panel, (2) is the deployment hinge, (3) is the deployment prevention device, (4) is the spacer,
(5) is the satellite itself.
次に動作について説明する。第１図（ａ）に示すように
人工衛星の打上げ時には、パネル（１）は展開ヒンジ（
２）を介して連結され、衛星本体に取りつけられ、スペ
ーサー（４）をパネル間にはさんで、展開防止装置（３
）により人工衛星側壁に収納されている。Next, the operation will be explained. As shown in Figure 1(a), when a satellite is launched, the panel (1) is attached to the deployable hinge (
2), is attached to the satellite body, and the spacer (4) is sandwiched between the panels, and the deployment prevention device (3) is attached to the satellite body.
) is housed in the side wall of the satellite.
人工衛星が軌道上に達した後、展開防止装置（３）を解
放することにより展開ヒンジ（２）に設けた展開ばねの
ばね力によりパネル（１）が展開し、第１図（ｂ）の形
態をとるものである。After the satellite reaches orbit, by releasing the deployment prevention device (3), the panel (1) is deployed by the spring force of the deployment spring provided on the deployment hinge (2), and the panel (1) is deployed as shown in Figure 1 (b). It takes a form.
従来の展開構造物は以上のように構成されているため、
展開後にもスペーサー（４）がパネル面上に残ってしま
うため、スペーサ−（４）をパネル端に配置していた。Since conventional deployable structures are configured as described above,
Since the spacer (4) remains on the panel surface even after deployment, the spacer (4) was placed at the edge of the panel.
ところが打上げ時の振動により各パネル（１）が互いに
衝突し、パネル面上に損傷を与えるという欠点があった
。However, there was a drawback in that the panels (1) collided with each other due to vibrations during launch, causing damage to the panel surfaces.
この発明はこの欠点を改善するためになされたもので、
パネルに一端がパネル端に固定され、数本のパネル幅の
スペーサーを取り付けた２枚の板ばねを取り付けること
によシバネル間の衝突をふせぎ、かつ展開後にパネル面
上にスペーサーが残らないようにした展開構造物を提供
するものである。This invention was made to improve this drawback.
By attaching two leaf springs to the panel, one end of which is fixed to the panel edge and several panel-width spacers attached, we prevent collisions between the panels and prevent spacers from remaining on the panel surface after deployment. The purpose of this invention is to provide a deployable structure.
以下この発明の一実施例を図によって説明する。An embodiment of the present invention will be described below with reference to the drawings.
第２図（ａ）において（１）はパネル、（２）は展開ヒ
ンジ、（３）は展開防止装置、（４）はスペーサー、（
５）は人工衛星本体、（６）は渦巻き型板ばねである。In Figure 2 (a), (1) is a panel, (2) is a deployment hinge, (3) is a deployment prevention device, (4) is a spacer, (
5) is the satellite body, and (6) is a spiral leaf spring.
展開防止機構（３）を解放することによりパネルは展開
し、スペーサー（４）は渦巻き型板ばね（６）によシ巻
き取られ、第２図（ｂ）の形態をとるものである。By releasing the deployment prevention mechanism (3), the panel is deployed, and the spacer (4) is wound up by the spiral leaf spring (6), taking the form shown in FIG. 2(b).
第８図により、スペーサー（４）と渦巻き型板ば、（６
）は渦巻き型板ばねである。According to Fig. 8, the spacer (4) and the spiral plate (6)
) is a spiral leaf spring.
第３図（ａ）はパネルが展開する前の状態を示す。スペ
ーサ（４）は渦巻き型板ばね（６）でつながれ。FIG. 3(a) shows the state before the panel is unfolded. The spacer (4) is connected by a spiral leaf spring (6).
パネル間に平行に並んでいる。渦巻き型板ばね（６）は
一端がパネル端に固定されている。The panels are arranged parallel to each other. One end of the spiral leaf spring (6) is fixed to the panel edge.
第８図（ｂ）に示すように、パネルの展開により渦巻き
型板ばね（６）は元の形に戻りはじめる。As shown in FIG. 8(b), the spiral leaf spring (6) begins to return to its original shape as the panel unfolds.
最終的に第８図（ｃ）に示すように、渦巻き型板ばね（
６）はパネルの外にスペーサー（４）を巻き取るこのよ
うな構造となっているため、収納時におけるパネル間の
衝突をふせぎ、パネル面に損傷を与えない。また展開後
はスペーサーはパネル面上から取り除かれるため、展開
構造物の機能にも影響を与えないという効果がある。Finally, as shown in Figure 8(c), a spiral leaf spring (
6) has such a structure in which the spacer (4) is wound around the outside of the panel, thereby preventing collision between the panels during storage and preventing damage to the panel surface. Furthermore, since the spacer is removed from the panel surface after deployment, it has the effect of not affecting the functionality of the deployment structure.
第１図は従来の展開型構造物の収納時、展開後を示す図
、第２図はこの発明による展開構造物の収納時、展開後
を示す図、第３図はこの発明による展開構造物の動作を
示す図である。
図中（１）はパネル、＜２）は展開ヒンジ、（３）は展
開防止装置、（４）はスペーサー、（５）は人工衛星本
体、（６）は渦巻き型板はねである。なお１図中同一あ
るいは相当部分については同一符号を付して示しである
。
代理人 葛 野 信 −
！＠ １ 図
第 ２ 図
（α）
＠３ 図
（Ｃ）FIG. 1 is a diagram showing a conventional deployable structure when stored and after deployment; FIG. 2 is a diagram showing a deployable structure according to the present invention when stored and after deployment; FIG. 3 is a diagram showing a deployable structure according to the present invention. FIG. In the figure, (1) is the panel, <2) is the deployment hinge, (3) is the deployment prevention device, (4) is the spacer, (5) is the satellite body, and (6) is the spiral plate flap. Note that the same or corresponding parts in FIG. 1 are designated by the same reference numerals. Agent Shin Kuzuno −! @1 Figure 2 (α) @3 Figure (C)
Claims (1)
に折りたたまれ展開した状態においてその機能をはだす
展開構造物において、パネルが折りたたまれた状態にお
いてパネル間の衝突をふせぐために、一端がパネル端に
固定された渦巻型の２枚の板ばねによってつながれた複
数本の上記パネルと同じ幅のスペーサーをパネル間には
さみ、パネルの展開過程において上記板ばねが元の渦巻
型になるようにパネル端に巻き取られることによシ、ス
ペーサーもそれとともにパネル面上から取り除かれるよ
うに構成したことを特徴とする人工衛星搭載展開構造物
。In a deployable structure that is made up of multiple flat panels and is folded into a folding screen shape when stored and performs its function when unfolded, one end of the panel is folded to prevent collisions between the panels when folded. A spacer of the same width as the plurality of above-mentioned panels connected by two spiral-shaped leaf springs fixed at the ends is sandwiched between the panels, and the panels are made so that the above-mentioned leaf springs return to their original spiral shape during the unfolding process of the panel. An artificial satellite-mounted deployable structure characterized in that the spacer is also removed from the panel surface by being rolled up at the end.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP57098902A JPS58214500A (en) | 1982-06-09 | 1982-06-09 | Unfolding structure loaded on artificial satellite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP57098902A JPS58214500A (en) | 1982-06-09 | 1982-06-09 | Unfolding structure loaded on artificial satellite |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS58214500A true JPS58214500A (en) | 1983-12-13 |
Family
ID=14232056
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP57098902A Pending JPS58214500A (en) | 1982-06-09 | 1982-06-09 | Unfolding structure loaded on artificial satellite |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS58214500A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2822803A1 (en) * | 2001-03-29 | 2002-10-04 | Cit Alcatel | SOLAR GENERATOR STRUCTURE FOR SATELLITE COMPRISING TIMING BETWEEN PANELS |
| FR2837168A1 (en) * | 2002-03-15 | 2003-09-19 | Mitsubishi Electric Corp | Satellite deployment structure, e.g. antenna for satellite, comprises elastic insertion member for prevention of vibration disposed in clearance between each panels |
-
1982
- 1982-06-09 JP JP57098902A patent/JPS58214500A/en active Pending
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2822803A1 (en) * | 2001-03-29 | 2002-10-04 | Cit Alcatel | SOLAR GENERATOR STRUCTURE FOR SATELLITE COMPRISING TIMING BETWEEN PANELS |
| WO2002079034A1 (en) * | 2001-03-29 | 2002-10-10 | Alcatel | Satellite solar generator structure comprising bracing elements between panels |
| US6909042B2 (en) | 2001-03-29 | 2005-06-21 | Alcatel | Satellite solar generator structure comprising bracing elements between panels |
| FR2837168A1 (en) * | 2002-03-15 | 2003-09-19 | Mitsubishi Electric Corp | Satellite deployment structure, e.g. antenna for satellite, comprises elastic insertion member for prevention of vibration disposed in clearance between each panels |
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