JPH05270498A - Satellite - Google Patents
SatelliteInfo
- Publication number
- JPH05270498A JPH05270498A JP6542992A JP6542992A JPH05270498A JP H05270498 A JPH05270498 A JP H05270498A JP 6542992 A JP6542992 A JP 6542992A JP 6542992 A JP6542992 A JP 6542992A JP H05270498 A JPH05270498 A JP H05270498A
- Authority
- JP
- Japan
- Prior art keywords
- satellite
- heat
- reflector
- reflecting mirror
- antenna
- 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
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- Aerials With Secondary Devices (AREA)
- Details Of Aerials (AREA)
Abstract
Description
【０００１】[0001]
【産業上の利用分野】この発明は、例えば放送衛星や通
信衛星等の各種衛星に供される人工衛星に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an artificial satellite used for various satellites such as broadcasting satellites and communication satellites.
【０００２】[0002]
【従来の技術】人類が宇宙空間に打上げた人工衛星は、
現在までのところ千数百機を越えている。この人工衛星
は、大半のものが設計寿命を終えて、その残存燃料がな
くなり、自力による軌道変更が困難となると、通常、回
収することなく、宇宙空間を漂った状態で放置される。
このような放置状態の人工衛星は、スペースデブリと称
され、比較的低い軌道を飛翔するものにあっては、寿命
が終了した後、長期間をかけて空気により減速され、最
終的に大気圏に突入して燃焼されることにより、消滅さ
れる。2. Description of the Related Art Artificial satellites launched by humanity into outer space
So far, there are more than a few hundred machines. When most of the artificial satellites have reached the end of their designed life and the remaining fuel is exhausted and it is difficult to change the orbit by themselves, they are usually left in the state of floating in outer space without being recovered.
Such an artificial satellite in a neglected state is called space debris, and if it flies in a relatively low orbit, it will be decelerated by air over a long period of time after the end of its life, and eventually it will enter the atmosphere. It disappears when it rushes and burns.
【０００３】しかしながら、上記スペースデブリと称す
る人工衛星にあっては、全てが燃え尽きることなく、機
体の一部が地球上に落下するという虞も有しており、非
常に危険なものである。これは、かつてのスカイラブと
称する宇宙実験基地の落下という実例がある。また、原
子炉を搭載した人工衛星にあっては、大気圏突入の際に
原子炉が崩壊されて放射能がばらまかれて放射能汚染を
起こす虞を有する。However, in the artificial satellite called space debris, there is a risk that all of the spacecraft will not burn out and a part of the body will fall onto the earth, which is extremely dangerous. There is an example of this being the fall of a space test station called Skylab. Further, in a satellite equipped with a nuclear reactor, there is a possibility that the nuclear reactor may be collapsed at the time of entry into the atmosphere and the radioactivity may be scattered to cause radioactive contamination.
【０００４】そこで、設計寿命を終了した人工衛星を安
全に回収することが考えられるが、これによると、回収
時に衛星本体の熱保護を行うための専用の耐熱装置を備
えなければならないために、非常に高価となるという問
題を有する。Therefore, it is conceivable to safely recover an artificial satellite whose design life has expired. According to this method, however, a dedicated heat-resistant device for protecting the heat of the satellite body at the time of recovery must be provided. It has the problem of being very expensive.
【０００５】[0005]
【発明が解決しようとする課題】以上述べたように、従
来の人工衛星では、設計寿命が終了した状態で、宇宙空
間に放置されるために、非常に危険であるという問題を
有していた。As described above, the conventional artificial satellite has a problem that it is extremely dangerous because it is left in outer space after the design life is finished. ..
【０００６】この発明は上記の事情に鑑みてなされたも
ので、構成簡易にして、簡便な衛星回収システムの構築
を実現し得るようにした人工衛星を提供することを目的
とする。The present invention has been made in view of the above circumstances, and it is an object of the present invention to provide an artificial satellite having a simple structure and capable of realizing the construction of a simple satellite recovery system.
【０００７】[0007]
【課題を解決するための手段】この発明は、一方面にパ
ラボラ形状の反射鏡面が設けられ、他方面に熱遮蔽用耐
熱面が設けられたアンテナ反射鏡と、このアンテナ反射
鏡が着脱自在に配設される衛星本体と、前記アンテナ反
射鏡を、その反射鏡面側あるいは耐熱面側のいずれか一
方を前記衛星本体に対向させて取付ける反射鏡支持手段
とを備えて人工衛星を構成したものである。According to the present invention, an antenna reflector having a parabolic reflector surface on one side and a heat-shielding heat-resistant surface on the other side, and the antenna reflector are detachable. An artificial satellite comprising a satellite main body to be provided and a reflector supporting means for mounting the antenna reflecting mirror so that either one of the reflecting mirror surface side and the heat resistant surface side is opposed to the satellite main body. is there.
【０００８】[0008]
【作用】上記構成によれば、アンテナ反射鏡は、衛星本
体に対して耐熱面側を対向した状態で取付けることによ
り、反射鏡面を用いた電波の送受が可能となり、その反
射鏡面側を衛星本体に対向させて取付けることにより、
該衛星本体を耐熱面で覆い、熱遮蔽を実行する。これに
より、衛星回収専用の耐熱装置を備えることなく、電波
の送受を実行するためのアンテナ反射鏡を利用した簡易
な衛星回収が実施可能となる。According to the above structure, the antenna reflecting mirror can be transmitted and received using the reflecting mirror surface by mounting the antenna reflecting mirror with the heat-resistant surface side facing the satellite body. By mounting it facing
The satellite body is covered with a heat-resistant surface to perform heat shielding. As a result, it is possible to perform a simple satellite recovery using an antenna reflector for transmitting and receiving radio waves without providing a heat-resistant device dedicated to satellite recovery.
【０００９】[0009]
【実施例】以下、この発明の実施例について、図面を参
照して詳細に説明する。Embodiments of the present invention will be described below in detail with reference to the drawings.
【００１０】図１はこの発明の一実施例に係る人工衛星
を示すもので、衛星本体１０にはアンテナ反射鏡１１が
着脱自在に配設される。このアンテナ反射鏡１１は、そ
の一方面にパラボラ形状の反射鏡面１１ａが形成され、
その他方面には、図２に示すように例えば耐熱タイルを
張付けた耐熱面１１ｂが形成される。そして、このアン
テナ反射鏡１１は、衛星本体１０に対して支持構体１２
（図１中では、図の都合上、図示せず、図３参照）を介
して、その反射鏡面側あるいは耐熱面側が着脱自在に取
付けられる。FIG. 1 shows an artificial satellite according to an embodiment of the present invention, and an antenna reflecting mirror 11 is detachably arranged on a satellite body 10. The antenna reflecting mirror 11 has a parabolic reflecting mirror surface 11a formed on one surface thereof,
On the other side, as shown in FIG. 2, a heat-resistant surface 11b to which heat-resistant tiles are attached is formed, for example. The antenna reflecting mirror 11 is provided with a support structure 12 for the satellite body 10.
The reflecting mirror surface side or the heat resistant surface side is detachably attached via (not shown in FIG. 1 for convenience of illustration, see FIG. 3).
【００１１】なお、図１中において、１３は太陽電池パ
ドルで、例えば衛星本体１０の周壁部に折畳み展開自在
に配設される。１４は一次放射器で、アンテナ反射鏡１
１の反射鏡面１１ａに対向配置される。In FIG. 1, numeral 13 is a solar cell paddle, which is foldably arranged on the peripheral wall of the satellite body 10, for example. 14 is a primary radiator, which is an antenna reflector 1
It is arranged so as to face the first reflecting mirror surface 11a.
【００１２】上記構成において、所定の軌道に投入され
た衛星本体１０には、アンテナ反射鏡１１が、その耐熱
面側を対向させた状態で、支持構体１２を介して配設さ
れると共に、太陽電池パドル１３が展開され、所定の運
用に供される。In the above-mentioned structure, the satellite reflecting body 11 placed in a predetermined orbit is provided with the antenna reflecting mirror 11 with the heat resistant surfaces thereof facing each other through the supporting structure 12 and the sun. The battery paddle 13 is developed and provided for a predetermined operation.
【００１３】そして、衛星寿命が終了して、衛星回収を
実行する場合には、先ず、アンテナ反射鏡１１が、衛星
本体１０から一旦、離脱されて、その反射鏡面側が衛星
本体１０に対向され、再び支持構体１２を用いて衛星本
体１０に取付けられる。同時に、太陽電池パドル１３が
衛星本体１０の周壁に折畳み収容される。ここで、衛星
本体１０は、その全体がアンテナ反射鏡１１の耐熱面１
１ｂで覆われた状態で、例えば大気圏に突入して地球に
帰還される。この際、衛星本体１０は、アンテナ反射鏡
１１が、エアロキャプチャーとして作用し、その周壁が
耐熱面１１ｂにより熱から保護されて、燃焼することな
く、安全に地上に帰還される。When the life of the satellite is over and the satellite is recovered, the antenna reflecting mirror 11 is first detached from the satellite main body 10 and the reflecting mirror side is opposed to the satellite main body 10. It is attached to the satellite body 10 again using the support structure 12. At the same time, the solar cell paddle 13 is folded and accommodated in the peripheral wall of the satellite body 10. Here, the entire satellite body 10 has a heat-resistant surface 1 of the antenna reflector 11.
In the state of being covered with 1b, for example, it rushes into the atmosphere and is returned to the earth. At this time, in the satellite body 10, the antenna reflecting mirror 11 acts as an aerocapture, and its peripheral wall is protected from heat by the heat-resistant surface 11b, and is safely returned to the ground without burning.
【００１４】このように、上記人工衛星は、一方面にパ
ラボラ形状の反射鏡面１１ａが設けられ、他方面に熱遮
蔽用耐熱面１１ｂが設けられたアンテナ反射鏡１１を備
え、このアンテナ反射鏡１１を衛星本体１０に対して耐
熱面側を対向させた状態で取付けることにより、反射鏡
面１１ａを用いた電波の送受を実行可能とし、その反射
鏡面側を衛星本体１０に対向させて取付けることによ
り、その耐熱面１１ｂで衛星本体１０を覆い、熱保護を
可能とするように構成した。これによれば、衛星回収専
用の耐熱装置を備えることなく、電波送受用のアンテナ
反射鏡１１を利用して大気圏再突入時における熱から衛
星本体１０を確実に保護することが可能な衛星回収シス
テムの構築が実現される。また、これによれば、原子炉
を搭載した衛星システムに適用することにより、宇宙空
間の放射能汚染を確実に防止することが可能となること
により、宇宙空間の安全性の向上が図れる。As described above, the artificial satellite includes the antenna reflecting mirror 11 having the parabolic reflecting mirror surface 11a provided on one side and the heat-shielding heat-resistant surface 11b provided on the other side. Is mounted with the heat-resistant surface side facing the satellite body 10, enabling transmission and reception of radio waves using the reflecting mirror surface 11a, and by mounting the reflecting mirror surface side facing the satellite body 10. The heat resistant surface 11b covers the satellite body 10 so as to enable heat protection. According to this, the satellite recovery system capable of reliably protecting the satellite body 10 from the heat at the time of reentry into the atmosphere by using the antenna reflecting mirror 11 for transmitting and receiving radio waves without providing a heat-resistant device dedicated to satellite recovery Is realized. Further, according to this, by applying it to a satellite system equipped with a nuclear reactor, it becomes possible to reliably prevent radioactive contamination of outer space, thereby improving the safety of outer space.
【００１５】なお、上記実施例では、衛星回収時に太陽
電池パドル１３を衛星本体１０の周壁に折畳み収容する
ように構成した場合で説明したが、これに限ることな
く、衛星回収時、太陽電池パドル１３を、例えば宇宙空
間に放出するように構成しても良い。よって、この発明
は、上記実施例に限ることなく、その他、この発明の要
旨を逸脱しない範囲で種々の変形を実施し得ることは勿
論である。In the above embodiment, the solar cell paddle 13 is folded and housed in the peripheral wall of the satellite body 10 at the time of satellite recovery, but the present invention is not limited to this. 13 may be configured to emit into outer space, for example. Therefore, the present invention is not limited to the above-described embodiments, and it is needless to say that various modifications can be made without departing from the scope of the present invention.
【００１６】[0016]
【発明の効果】以上詳述したように、この発明によれ
ば、構成簡易にして、簡便な衛星回収システムの構築を
実現し得るようにした人工衛星を提供することができ
る。As described above in detail, according to the present invention, it is possible to provide an artificial satellite having a simple structure and capable of realizing the construction of a simple satellite recovery system.
【図１】この発明の一実施例に係る人工衛星の運用状態
を示した図。FIG. 1 is a diagram showing an operational state of an artificial satellite according to an embodiment of the present invention.
【図２】図１のアンテナ反射鏡を取り出して示した図。FIG. 2 is a diagram showing the antenna reflecting mirror of FIG. 1 taken out.
【図３】図１の回収状態を示した図。FIG. 3 is a view showing a recovery state of FIG.
１０…衛星本体、１１…アンテナ反射鏡、１１ａ…反射
鏡面、１１ｂ…耐熱面、１２…支持構体、１３…太陽電
池パドル、１４…一次放射器。10 ... Satellite main body, 11 ... Antenna reflecting mirror, 11a ... Reflecting mirror surface, 11b ... Heat resistant surface, 12 ... Support structure, 13 ... Solar cell paddle, 14 ... Primary radiator.
Claims (1)
られ、他方面に熱遮蔽用耐熱面が設けられたアンテナ反
射鏡と、 このアンテナ反射鏡が着脱自在に配設される衛星本体
と、 前記アンテナ反射鏡を、その反射鏡面側あるいは耐熱面
側のいずれか一方を前記衛星本体に対向させて取付ける
反射鏡支持手段とを具備したことを特徴とする人工衛
星。1. An antenna reflector having a parabolic reflector surface on one surface and a heat-shielding heat-resistant surface on the other surface, and a satellite body to which the antenna mirror is detachably mounted. An artificial satellite comprising: a reflector supporting means for mounting the antenna reflector with one of the reflector surface side and the heat resistant surface side facing the satellite body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP6542992A JPH05270498A (en) | 1992-03-24 | 1992-03-24 | Satellite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP6542992A JPH05270498A (en) | 1992-03-24 | 1992-03-24 | Satellite |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH05270498A true JPH05270498A (en) | 1993-10-19 |
Family
ID=13286843
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP6542992A Pending JPH05270498A (en) | 1992-03-24 | 1992-03-24 | Satellite |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH05270498A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2010247719A (en) * | 2009-04-17 | 2010-11-04 | Mitsubishi Heavy Ind Ltd | Composite material for spacecraft and fuel tank |
| 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 |
| WO2020157807A1 (en) * | 2019-01-28 | 2020-08-06 | 三菱電機株式会社 | Satellite constellation formation system, satellite constellation formation method, debris removal scheme, satellite constellation construction scheme, and ground equipment |
-
1992
- 1992-03-24 JP JP6542992A patent/JPH05270498A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2010247719A (en) * | 2009-04-17 | 2010-11-04 | Mitsubishi Heavy Ind Ltd | Composite material for spacecraft and fuel tank |
| 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 |
| WO2020157807A1 (en) * | 2019-01-28 | 2020-08-06 | 三菱電機株式会社 | Satellite constellation formation system, satellite constellation formation method, debris removal scheme, satellite constellation construction scheme, and ground equipment |
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