JPH0585496A - Attitude adjusting device - Google Patents
Attitude adjusting deviceInfo
- Publication number
- JPH0585496A JPH0585496A JP3245836A JP24583691A JPH0585496A JP H0585496 A JPH0585496 A JP H0585496A JP 3245836 A JP3245836 A JP 3245836A JP 24583691 A JP24583691 A JP 24583691A JP H0585496 A JPH0585496 A JP H0585496A
- Authority
- JP
- Japan
- Prior art keywords
- attitude
- satellite
- artificial satellite
- communication antenna
- freedom
- 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.)
- Withdrawn
Links
Landscapes
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
- Manipulator (AREA)
Abstract
Description
【０００１】[0001]
【産業上の利用分野】本発明は人工衛星等における指向
性機器の姿勢調整装置に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a posture adjusting device for a directional device in an artificial satellite or the like.
【０００２】[0002]
【従来の技術】図２は従来の人工衛星の概略組立図であ
る。１１は人工衛星、２は衛星本体、３，４はそれぞれ
指向性機器である太陽電池パドルと通信アンテナであ
る。太陽電池パドル３と通信アンテナ４はそれぞれ衛星
本体２と一自由度又は二自由度の連結棒８で結合されて
いる。マニピュレータ６でマニピュレータ先端負荷７を
移動させるときなど、衛星本体２の姿勢が変動する場
合、連結棒８だけでは太陽電池パドル３や通信アンテナ
４の姿勢を一定に保持することは不可能で、別途姿勢制
御機器を設置するか噴射ジェットを作動させることによ
り衛星本体２の姿勢を一定に保持している。2. Description of the Related Art FIG. 2 is a schematic assembly diagram of a conventional artificial satellite. Reference numeral 11 is an artificial satellite, 2 is a satellite body, and 3 and 4 are solar cell paddles and communication antennas, which are directional devices. The solar cell paddle 3 and the communication antenna 4 are connected to the satellite body 2 by a connecting rod 8 having one or two degrees of freedom. When the attitude of the satellite body 2 changes, for example, when the manipulator tip load 7 is moved by the manipulator 6, it is impossible to keep the attitude of the solar cell paddle 3 and the communication antenna 4 constant only by the connecting rod 8, and separately. The attitude of the satellite body 2 is maintained constant by installing attitude control equipment or operating the jet jet.
【０００３】[0003]
【発明が解決しようとする課題】上記従来の人工衛星の
姿勢調整手段には解決すべき次の課題があった。The above-mentioned conventional attitude adjusting means for the artificial satellite has the following problems to be solved.
【０００４】即ち、指向性機器の姿勢を一定に保持する
ために別途姿勢制御機器を使用する場合、比較的多量の
電力を必要とし、人工衛星搭載機器へ配分する電力が減
少するという問題があった。That is, when a separate attitude control device is used to keep the attitude of the directional device constant, a relatively large amount of power is required, and there is a problem that the amount of power distributed to the device mounted on the satellite decreases. It was
【０００５】また噴射ジェットを使用すれば貴重な燃料
が消費され、人工衛星の作動寿命が減少するという問題
があった。Further, if the injection jet is used, there is a problem that valuable fuel is consumed and the operational life of the artificial satellite is shortened.
【０００６】本発明は上記問題を解決した、姿勢制御機
器や噴射ジェットを用いることなく指向性機器の一定姿
勢を保てる姿勢調整装置を提供することを目的とする。An object of the present invention is to provide a posture adjusting device which can solve the above problems and can maintain a constant posture of a directional device without using a posture control device or an injection jet.
【０００７】[0007]
【課題を解決するための手段】本発明は上記構成の解決
手段として、一端を人工衛星等の本体に連結され他端
を、空間に対し一定姿勢を求められる太陽電池パネル、
通信アンテナ等の指向性機器に連結されると共に人工衛
星等の本体の３自由度の変動に対し、等量逆向きに変動
して指向性機器の空間姿勢を一定に保持してなることを
特徴とする姿勢調整装置を提供しようとするものであ
る。As a means for solving the above-mentioned problems, the present invention provides a solar cell panel, one end of which is connected to a main body of an artificial satellite or the like and the other end of which is required to have a constant posture in space.
It is connected to a directional device such as a communication antenna and changes in the opposite direction by an equal amount with respect to changes in the three degrees of freedom of the main body such as an artificial satellite, and maintains the spatial posture of the directional device constant. The present invention aims to provide a posture adjusting device.
【０００８】[0008]
【作用】本発明は上記のように構成されるので次の作用
を有する。Since the present invention is constructed as described above, it has the following actions.
【０００９】即ち、人工衛星の本体と指向性機器との間
に介在し、人工衛星の本体の３自由度の変動に対し、等
量逆向きに変動するため、たとえば人工衛星に搭載した
マニピュレータ等の動作により衛星本体の姿勢が変動し
ても、姿勢調整装置が変動を打ち消す方向に作動する。
この結果、太陽電池パドル及び通信アンテナ等の指向性
機器の姿勢が一定に保たれる。That is, since it intervenes between the main body of the artificial satellite and the directional device and changes in the opposite direction by an equal amount with respect to changes in the three degrees of freedom of the main body of the artificial satellite, for example, a manipulator mounted on the artificial satellite or the like. Even if the attitude of the satellite body fluctuates due to the above operation, the attitude adjustment device operates in a direction to cancel the fluctuation.
As a result, the attitude of the directional device such as the solar cell paddle and the communication antenna is kept constant.
【００１０】[0010]
【実施例】本発明の一実施例に係る姿勢調整装置を図１
により説明する。なお、従来例の図２と同様の構成部材
には同符号を付し、必要ある場合を除き、説明を省略す
る。DESCRIPTION OF THE PREFERRED EMBODIMENTS FIG. 1 shows a posture adjusting device according to an embodiment of the present invention.
Will be explained. The same components as those of the conventional example shown in FIG. 2 are designated by the same reference numerals, and the description thereof will be omitted unless necessary.
【００１１】図１は本実施例の姿勢調整装置を備えた人
工衛星の斜視図で、１が人工衛星、２が衛星本体、３，
４がそれぞれ指向性機器である太陽電池パドルと通信ア
ンテナである。太陽電池パドル３と通信アンテナ４はそ
れぞれ衛星本体２と３自由度もしくはそれ以上の自由度
の姿勢調整装置５で結合されている。６はマニピュレー
タ、７はマニピュレータ先端負荷である。マニピュレー
タ６でマニピュレータ先端負荷７を移動する場合など衛
星本体２の姿勢が変動するが姿勢調整装置５がその逆向
きに連動して太陽電池パドル３や通信アンテナ４など指
向性機器の姿勢は一定に保持される。FIG. 1 is a perspective view of an artificial satellite equipped with the attitude adjusting device of the present embodiment. 1 is an artificial satellite, 2 is a satellite body, and 3,
4 is a solar cell paddle and a communication antenna, which are directional devices. The solar cell paddle 3 and the communication antenna 4 are connected to the satellite body 2 by an attitude adjusting device 5 having three or more degrees of freedom, respectively. 6 is a manipulator, and 7 is a manipulator tip load. When the manipulator 6 moves the manipulator tip load 7, the attitude of the satellite body 2 changes, but the attitude adjusting device 5 works in the opposite direction to make the attitude of the directional equipment such as the solar cell paddle 3 and the communication antenna 4 constant. Retained.
【００１２】以上の通り本実施例によれば、空間におい
てたとえば衛星本体２が、マニピュレータ先端負荷７の
移動等の避けられない理由によって姿勢を変えても、太
陽電池パドル３や通信アンテナ４との間に介在する３自
由度以上の自由度を持つ姿勢調整装置５が、衛星本体２
の伝達する３次元方向の動きに対し、等量逆向きの動き
をなすので太陽電池パドル３及び通信アンテナ４は衛星
本体２の動きに全く影響されず、一定姿勢を維持できる
という利点を有する。As described above, according to this embodiment, even if the attitude of the satellite body 2 is changed in space due to an unavoidable reason such as movement of the manipulator tip load 7, the space between the satellite paddle 3 and the communication antenna 4 is changed. The attitude adjusting device 5 having three or more degrees of freedom interposed between the satellite body 2
Since the movement in the opposite direction is the same as the movement in the three-dimensional direction transmitted by, the solar cell paddle 3 and the communication antenna 4 have the advantage that they can be maintained in a fixed attitude without being affected by the movement of the satellite body 2.
【００１３】また、姿勢調整装置５は、たとえば３自由
度の各自由度については衛星本体２より伝わるそれぞれ
の１自由度に対してのみ等量逆向きの動作を行なえばよ
いのであるから、入力から動作に至るプロセスがきわめ
て単純で、姿勢制御装置などのように多量の電力を消費
しないという利点がある。Further, the attitude adjusting device 5 is required to perform an operation in the opposite direction by an equal amount only for each one degree of freedom transmitted from the satellite body 2 for each degree of freedom, for example, three degrees of freedom. The process from to movement is extremely simple, and there is an advantage that a large amount of power is not consumed unlike the attitude control device.
【００１４】また、姿勢調整装置５は噴射ジェットを用
いないので貴重な燃料を消費することがなく、従って人
工衛星の作動寿命を短縮する懸念がないという利点があ
る。Further, since the attitude adjusting device 5 does not use an injection jet, it does not consume valuable fuel, and therefore there is an advantage that there is no concern of shortening the operating life of the artificial satellite.
【００１５】[0015]
【発明の効果】本発明は上記のように構成されるので次
の効果を有する。Since the present invention is constructed as described above, it has the following effects.
【００１６】即ち、本発明によれば姿勢調整装置の作動
により、衛星本体の姿勢変動を許容しながら指向性機器
の姿勢を一定に保つことができると同時に衛星本体の姿
勢制御機器消費電力、噴射ジェット消費量を低減するこ
とができる。That is, according to the present invention, by operating the attitude adjusting device, the attitude of the directional device can be kept constant while allowing the attitude change of the satellite main body, and at the same time the attitude control device power consumption and injection of the satellite main body. Jet consumption can be reduced.
【図１】本発明の一実施例に係る姿勢調整装置を備えた
人工衛星の斜視図である。FIG. 1 is a perspective view of an artificial satellite including an attitude adjusting device according to an embodiment of the present invention.
【図２】従来の人工衛星の斜視図である。FIG. 2 is a perspective view of a conventional artificial satellite.
１ 人工衛星 ２ 衛星本体 ３ 太陽電池パドル ４ 通信アンテナ ５ 姿勢調整装置 ６ マニピュレータ ７ マニピュレータ先端負荷 1 artificial satellite 2 satellite body 3 solar array paddle 4 communication antenna 5 attitude adjustment device 6 manipulator 7 manipulator tip load
───────────────────────────────────────────────────── フロントページの続き (72)発明者 川村 武也 神戸市兵庫区和田崎町一丁目１番１号 三 菱重工業株式会社神戸造船所内 (72)発明者 水落 道明 神戸市兵庫区和田崎町一丁目１番１号 三 菱重工業株式会社神戸造船所内 ─────────────────────────────────────────────────── ─── Continuation of the front page (72) Takeya Kawamura 1-1-1, Wadasaki-cho, Hyogo-ku, Kobe-shi Sanryo Heavy Industries Ltd. Kobe Shipyard (72) Michiaki Mizuochi Wadazaki-cho, Hyogo-ku, Kobe-shi 1-1-1 Sanryo Heavy Industries Ltd. Kobe Shipyard
Claims (1)
を、空間に対し一定姿勢を求められる太陽電池パネル、
通信アンテナ等の指向性機器に連結されると共に人工衛
星等の本体の３自由度の変動に対し、等量逆向きに変動
して指向性機器の空間姿勢を一定に保持してなることを
特徴とする姿勢調整装置。1. A solar cell panel, one end of which is connected to a body of an artificial satellite or the like and the other end of which is required to have a fixed attitude in space.
It is connected to a directional device such as a communication antenna, and changes in the opposite direction by an equal amount with respect to changes in the 3 degrees of freedom of the main body such as an artificial satellite, and maintains the spatial posture of the directional device constant. Posture adjustment device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP3245836A JPH0585496A (en) | 1991-09-25 | 1991-09-25 | Attitude adjusting device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP3245836A JPH0585496A (en) | 1991-09-25 | 1991-09-25 | Attitude adjusting device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH0585496A true JPH0585496A (en) | 1993-04-06 |
Family
ID=17139575
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP3245836A Withdrawn JPH0585496A (en) | 1991-09-25 | 1991-09-25 | Attitude adjusting device |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH0585496A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2018510090A (en) * | 2015-03-31 | 2018-04-12 | ワールドビュー・サテライツ・リミテッド | Satellite frame and method for manufacturing satellite |
-
1991
- 1991-09-25 JP JP3245836A patent/JPH0585496A/en not_active Withdrawn
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2018510090A (en) * | 2015-03-31 | 2018-04-12 | ワールドビュー・サテライツ・リミテッド | Satellite frame and method for manufacturing satellite |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| A300 | Withdrawal of application because of no request for examination |
Free format text: JAPANESE INTERMEDIATE CODE: A300 Effective date: 19981203 |