JPS62103298A - Method of stopping revolution of artificial satellite - Google Patents
Method of stopping revolution of artificial satelliteInfo
- Publication number
- JPS62103298A JPS62103298A JP60242900A JP24290085A JPS62103298A JP S62103298 A JPS62103298 A JP S62103298A JP 60242900 A JP60242900 A JP 60242900A JP 24290085 A JP24290085 A JP 24290085A JP S62103298 A JPS62103298 A JP S62103298A
- Authority
- JP
- Japan
- Prior art keywords
- satellite
- artificial satellite
- gas
- bag
- stopping
- 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
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
- Radio Relay Systems (AREA)
- Wind Motors (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】
〔発明の利用分野〕
本発明は人工衛星に係り、特に、宇宙空間に回転しなが
ら浮遊し自身では停止することができない人工衛星を停
止させるに好適な人工衛星回路停止方法に関する。[Detailed Description of the Invention] [Field of Application of the Invention] The present invention relates to artificial satellites, and in particular, to an artificial satellite circuit stoppage suitable for stopping an artificial satellite that is rotating and floating in outer space and cannot be stopped by itself. Regarding the method.
従来、人工衛星は、故障したり姿勢制御用燃料がなくな
った場合等には、寿命を終えたものとして宇宙空間にそ
のまま放置されていた。しかるに、スペースシャトルの
実現、スペースステーション計画の進捗等により、寿命
を終えた人工衛星を修理する等して再使用することが可
能になってきている。Conventionally, when an artificial satellite breaks down or runs out of fuel for attitude control, it is assumed that its lifespan has come to an end and is left alone in space. However, with the realization of the space shuttle and the progress of the space station project, it has become possible to repair and reuse artificial satellites that have reached the end of their lifespans.
一般に故障あるいは燃料切れになった人工衛星は回転運
動を起こしており、これを修理しあるいは燃料を補給す
るためには人工衛星を停止させる必要がある。しかし１
回転している質量の大きい人工衛星を無重量状態下で停
止させることは非常に困難であり、宇宙飛行士が人工衛
星にフックを引掛ける等して機械的に停止させることは
、人工衛星の質量が大きい程また回転速度が速い程危険
を伴う。（公知文献特開昭５９−１４９８９９号および
特開昭５９−１５６８９８号）。Generally, a satellite that has failed or run out of fuel is rotating, and in order to repair or refuel, it is necessary to stop the satellite. But 1
It is extremely difficult to stop a rotating, large-mass satellite in a weightless state, and it is difficult for astronauts to stop it mechanically, such as by hooking it to the satellite. The larger the mass and the faster the rotation speed, the more dangerous it becomes. (Known documents JP-A-59-149899 and JP-A-59-156898).
本発明の目的は、自身の姿勢制御システムでは停止不能
な人工衛星の回転運動を容易に停止させることができる
人工衛星回転停止方法を提供することにある。An object of the present invention is to provide a method for stopping the rotation of an artificial satellite that can easily stop the rotational motion of an artificial satellite that cannot be stopped by its own attitude control system.
地上に在る物体を回転させる場合、外部より回転に要す
るエネルギーを補給し続けないとやがて止まってしまう
。これは、地上に存在する空気が物体に接することによ
り、物体の回転エネルギーが摩擦熱として散逸してしま
うためである。そこで本発明ではこの現象を積極的に利
用し、空室空間に浮遊し自身の姿勢制御システムでは停
止不能になっている人工衛星を袋体内に収め、該袋体内
にガスを注入し、該ガスの抵抗により人工衛星の回転エ
ネルギーを熱エネルギーに変換して人工衛星を停止させ
る。When an object on the ground is rotated, it will eventually stop unless the energy required for rotation is continuously supplied from outside. This is because when the air on the ground comes into contact with the object, the rotational energy of the object is dissipated as frictional heat. Therefore, in the present invention, this phenomenon is actively utilized, and an artificial satellite that is floating in an empty space and cannot be stopped by its own attitude control system is housed in a bag, gas is injected into the bag, and the gas This resistance converts the rotational energy of the satellite into thermal energy and stops the satellite.
以下、本発明の一実施例を図面を参照して説明する。 Hereinafter, one embodiment of the present invention will be described with reference to the drawings.
第１図は、人工衛星の回転を停止させる方法を説明する
模式図である。先ず、本実施例ではスペースシャトル１
で目標とする人工衛星２に近づく。FIG. 1 is a schematic diagram illustrating a method for stopping the rotation of an artificial satellite. First, in this example, Space Shuttle 1
approach the target satellite 2.
次に１回転している人工衛星２に袋体３を被せ袋対３内
に人工衛星２を収納する。この作業は宇宙飛行士あるい
はシャトル搭載のリモートマニピュレータにより行なう
。そして、パイプ４を開いて袋体３内に空気等のガスを
注入する。これにより。Next, the bag body 3 is placed over the artificial satellite 2 which is rotating once, and the artificial satellite 2 is housed in the bag pair 3. This work is performed by astronauts or by remote manipulators on board the shuttle. Then, the pipe 4 is opened and gas such as air is injected into the bag body 3. Due to this.
人工衛星２の回転エネルギーは袋体３内のガスの熱エネ
ルギーに変換されて人工衛星２は徐々に停止する６人工
衛星２の回転速度が速くても長時間待機すれば必ず停止
する。またこの場合、ガス圧を上げて抵抗を大きくすれ
ば時間の短縮を図れる。The rotational energy of the satellite 2 is converted into the thermal energy of the gas inside the bag body 3, and the satellite 2 gradually stops.6 Even if the rotational speed of the satellite 2 is high, it will definitely stop if it stands by for a long time. In this case, the time can be shortened by increasing the gas pressure and increasing the resistance.
その後１１袋体３を裁断し、温度が上昇したガスを宇宙
空間に放出すると共に人工衛星２を取り出し。Thereafter, the 11 bags 3 are cut, the heated gas is released into space, and the satellite 2 is taken out.
これをリモートマニピュレータ５を使用してシャトル１
内に収納し故障を修理したり、燃料を供給し、再び宇宙
空間に放出して再稼働させる。Using remote manipulator 5, shuttle 1
The spacecraft is then stored inside the space, where malfunctions are repaired, fuel is supplied, and it is released back into space and restarted.
第２図は袋体の外観図で、第３図は第２図の■−■線断
図面である。袋体３は２分割構成でなり、膜６，７をフ
ァスナ部８，９で結合することにより１つの袋が形成さ
れる。膜６，７は強靭な可撓性材でなり、好ましく１袋
内部を透視できるように透明材である方がよい。膜６の
全周縁に一体成形されたファスナ部８には、第３図に示
すように、内部に空洞８′が形成されており、このファ
スナ部８に取り付けられているガスボンベ（図示せず）
からガスを空洞８′に注入すると、係合部１０が膨出形
成されるようになっている。膜７の全周縁に一体成形さ
れたファスナ部９には内部に空洞９′が形成されており
、このファスナ部９に取り付けられている図示しないガ
スボンベからガスを空洞９′に注入すると、前記係合部
１０に掛止する係合部１１が形成されるようになってい
る。係合部１０゜１１の形状を第３図の様にすると１袋
体３内の圧力が増すにつれてシール効果が生じる。膜７
の略中夫にはガス注入用アダプタ１２が取り付けてあり
、このアダプタ１２にパイプ４を接続する。FIG. 2 is an external view of the bag, and FIG. 3 is a cross-sectional view taken along the line ■--■ in FIG. The bag body 3 has a two-part structure, and one bag is formed by joining the membranes 6 and 7 with fastener parts 8 and 9. The membranes 6 and 7 are made of a strong and flexible material, preferably a transparent material so that the inside of one bag can be seen through. As shown in FIG. 3, the fastener part 8 integrally molded around the entire periphery of the membrane 6 has a cavity 8' formed therein, and a gas cylinder (not shown) attached to the fastener part 8 can be inserted into the fastener part 8, as shown in FIG.
When gas is injected into the cavity 8', the engaging portion 10 is bulged. A cavity 9' is formed inside the fastener part 9 integrally molded around the entire periphery of the membrane 7, and when gas is injected into the cavity 9' from a gas cylinder (not shown) attached to this fastener part 9, the above-mentioned engagement occurs. An engaging portion 11 that engages with the joint portion 10 is formed. If the shape of the engaging portions 10 and 11 is made as shown in FIG. 3, a sealing effect will be produced as the pressure within one bag body 3 increases. Membrane 7
A gas injection adapter 12 is attached to the middle end of the pipe, and the pipe 4 is connected to this adapter 12.
斯かる構成で成る袋体３を人工衛星に被せる場合、先ず
折りたたんである状態の膜６を取り出してそのファスナ
部８にガスを注入し、ファスナ部８をリング状にして（
第４図）これを人工衛星に被せる。そして、次に、折り
たたんである状態の股７を取り出してそのファスナ部９
をその係合部１１がファスナ部８の係合部１０に掛止す
るようにガスを注入して形成し、袋体３内に人工衛星を
収納する。尚、膜７のファスナ部９を先に形成し、これ
に膜６のファスナ部８を結合するようにしてもよい。When the bag body 3 having such a structure is to be placed on an artificial satellite, the membrane 6 in the folded state is first taken out, gas is injected into the fastener part 8, and the fastener part 8 is made into a ring shape (
Figure 4) Cover the artificial satellite with this. Next, take out the folded crotch 7 and zipper part 9.
is formed by injecting gas so that the engaging part 11 is hooked to the engaging part 10 of the fastener part 8, and the artificial satellite is housed in the bag body 3. Incidentally, the fastener part 9 of the membrane 7 may be formed first, and the fastener part 8 of the membrane 6 may be bonded thereto.
ガスをシャトル（第１図）からパイプ４を通して袋体３
内に注入し、人工衛星が停止するまで待機する。人工衛
星が停止した後、膜６を裁断し、ガスを宇宙空間に逃が
し、人工衛星の回りから袋体３を取り除く。人工衛星停
止後に袋体３内のガスを再びパイプ４を介して回収しな
いのは、膜６゜７が人工衛星にまとねり付くのを避ける
為である。Gas is passed from the shuttle (Fig. 1) through the pipe 4 to the bag body 3.
and wait until the satellite stops. After the satellite has stopped, the membrane 6 is cut, the gas is released into space, and the bag body 3 is removed from around the satellite. The reason why the gas inside the bag 3 is not recovered via the pipe 4 after the satellite is stopped is to prevent the membrane 6.7 from clumping around the satellite.
尚、膜６を裁断するのではなく、ファスナ部８または９
のガスを抜くことでファスナ部８，９間を分離するよう
にしてもよい。そして、両１１％６．７をシャトル内に
回収実る。Note that the membrane 6 is not cut, but the fastener part 8 or 9 is cut.
The fastener parts 8 and 9 may be separated by removing the gas. Then, both 11% and 6.7% were recovered into the shuttle.
本発明によれば、回転する人工衛星を外部から容易に停
止させることができる。According to the present invention, a rotating artificial satellite can be easily stopped from the outside.
第１図は本発明の一実施例による人工衛星回路停止方法
を説明する模式図、第２図は袋体の外観図、第３図は第
２図の■−■線断面図、第４図は袋体被覆説明図である
。
１・・・スペースシャトル、２・・・人工衛星、３・・
・袋体、４・・・パイプ、５・・・リモートマニピュレ
ータ、６．７・・・膜、８，９・・・ファスナ部、８’
、９’・・・空洞、１０，１１・・・係合部、１２・・
・ガス注入用アダプタ。
代理人 秋 本 正 実
第１図Fig. 1 is a schematic diagram illustrating a method for stopping an artificial satellite circuit according to an embodiment of the present invention, Fig. 2 is an external view of the bag body, Fig. 3 is a sectional view taken along the line ■-■ in Fig. 2, and Fig. 4 is an explanatory diagram of the bag covering. 1...Space shuttle, 2...Artificial satellite, 3...
・Bag body, 4... Pipe, 5... Remote manipulator, 6.7... Membrane, 8, 9... Fastener section, 8'
, 9'...Cavity, 10, 11...Engaging portion, 12...
・Gas injection adapter. Agent Tadashi Akimoto Figure 1
Claims (1)
になっている人工衛星を袋体内に収め、該袋体内にガス
を注入し、該ガスの抵抗により前記人工衛星の回転エネ
ルギーを熱エネルギーに変換して当該人工衛星を停止さ
せる人工衛星回転停止方法。An artificial satellite that is floating in outer space and cannot be stopped by its own attitude control system is housed in a bag, gas is injected into the bag, and the rotational energy of the satellite is converted into thermal energy by the resistance of the gas. A method for stopping the rotation of an artificial satellite by stopping the satellite.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP60242900A JPS62103298A (en) | 1985-10-31 | 1985-10-31 | Method of stopping revolution of artificial satellite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP60242900A JPS62103298A (en) | 1985-10-31 | 1985-10-31 | Method of stopping revolution of artificial satellite |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS62103298A true JPS62103298A (en) | 1987-05-13 |
Family
ID=17095886
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP60242900A Pending JPS62103298A (en) | 1985-10-31 | 1985-10-31 | Method of stopping revolution of artificial satellite |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS62103298A (en) |
-
1985
- 1985-10-31 JP JP60242900A patent/JPS62103298A/en active Pending
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