JPS58142000A - Connection system of artificial satellite - Google Patents
Connection system of artificial satelliteInfo
- Publication number
- JPS58142000A JPS58142000A JP57025176A JP2517682A JPS58142000A JP S58142000 A JPS58142000 A JP S58142000A JP 57025176 A JP57025176 A JP 57025176A JP 2517682 A JP2517682 A JP 2517682A JP S58142000 A JPS58142000 A JP S58142000A
- Authority
- JP
- Japan
- Prior art keywords
- connector
- satellite
- satellites
- attached
- 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.)
- Granted
Links
- 238000000034 method Methods 0.000 claims description 3
- 230000005291 magnetic effect Effects 0.000 claims description 2
- 239000003302 ferromagnetic material Substances 0.000 description 5
- 239000004020 conductor Substances 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000012544 monitoring process Methods 0.000 description 2
- 238000013459 approach Methods 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 239000006187 pill Substances 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
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/646—Docking or rendezvous systems
- B64G1/6462—Docking or rendezvous systems characterised by the means for engaging other vehicles
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Communication Cables (AREA)
- Details Of Connecting Devices For Male And Female Coupling (AREA)
- Details Of Television Systems (AREA)
- Prostheses (AREA)
- Input Circuits Of Receivers And Coupling Of Receivers And Audio Equipment (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】
〔発明の属する分野の説明〕
本発明は、軌道上にある複数個の無人の人工衛星を地上
でモニターしながら操作することによって、ケーブルに
より接続する方式に関するものである。[Detailed description of the invention] [Description of the field to which the invention pertains] The present invention relates to a method for connecting a plurality of unmanned satellites in orbit by cables by operating them while monitoring them on the ground. .
〔従来の技術の説明〕 □
従来、衛星の軌道上での相互接続は、情報伝送としての
無線通信が考えられているだけである。[Description of Prior Art] □ Conventionally, wireless communication for information transmission has only been considered for interconnection of satellites in orbit.
強いて言えば２個の有人衛星が人間の操Ｈによる直接の
ドグキング′が行われている。To put it bluntly, two manned satellites are being directly dogged by human operators.
また、宇゛宙発電所構想として宇宙空間で大規模に太陽
発電した大電力を地上にマイクロ波で伝送しようとする
構゛想がある。しか１、マイクロ波に゛より２つめ１Ｉ
ｌｉＪｉ間で電力を伝送するには、相互のｌＩ＃星に大
規模な装置を必要とするため、衛星の重量増加とともに
、熱制御等の計装装置が複雑化し、Ｐｋ術的かつ経済的
に容易でない。In addition, there is a space power plant concept in which a large amount of solar power is generated in space and transmitted to the ground using microwaves. But 1, the microwave is better than the 2nd 1I
Transmitting power between liJi requires large-scale equipment on each other's lI# stars, which increases the weight of the satellite and complicates instrumentation such as thermal control, making it both technically and economically difficult. It's not easy.
本発明は、複数個の無人の人工衛星を地上からのコマン
ド操作により、クープル接続する方式を提供することを
目的とする。An object of the present invention is to provide a method for couple-coupling a plurality of unmanned artificial satellites by command operation from the ground.
このための、接続用コネクタについては、従来のコネク
タでは一般にピ／！！続であるため使用することができ
ないので、宇宙空間で人間を介さすに接続および切離し
を確実に実施するだめのコネクタを提供する。Conventional connectors for this purpose generally use pin/! ! To provide a connector that can reliably connect and disconnect without human intervention in outer space since it cannot be used because it is connected.
本発明は、複数個の無人の人工衛星をケーブルにより接
続するにあたり、コイル状の接続ケーブルとコーン状の
コネクタを使用し、衛星に搭載したビジコンカメラでモ
ニターしながら、地上局からのコマンドにより軌道上□
の複数の衛星相互の接続および切離しを可能にしたもの
である。The present invention uses a coiled connection cable and a cone-shaped connector to connect multiple unmanned artificial satellites with a cable, and while monitoring with a vidicon camera mounted on the satellite, orbits are transmitted by commands from a ground station. Top□
This enabled the connection and disconnection of multiple satellites.
第１図は本発明の実施例構成図である。１はミッション
機器を搭載したミッション衛星、２はミッション衛星に
電力を供給する電力衛星、３はコイル状の接続ケーブル
、４は接続コネクタ、５および５′はビジコンカメラで
ある。FIG. 1 is a configuration diagram of an embodiment of the present invention. 1 is a mission satellite carrying mission equipment, 2 is a power satellite that supplies power to the mission satellite, 3 is a coiled connection cable, 4 is a connection connector, and 5 and 5' are vidicon cameras.
まずミッション衛星１と電力衛星２とを同時に膚たは別
々に所定の軌道に投入し、両画星を次第に接近させる。First, the mission satellite 1 and the power satellite 2 are placed into a predetermined orbit simultaneously or separately, and the satellites are gradually brought closer to each other.
適当な距離まで近づいたとき、格納してあったコイル状
のケーブル３をコイルの弾性を利用して伸長する。宇宙
空間では重力および空気抵抗等がないので、コイル状の
ケーブル３はその弾性によりたわむことはなく、所だの
長さに伸長することができる。When it approaches to an appropriate distance, the stored coiled cable 3 is extended using the elasticity of the coil. Since there is no gravity, air resistance, etc. in outer space, the coiled cable 3 does not bend due to its elasticity and can be extended to a certain length.
ミッション衛星１のケーブル３の先端には円すい状のお
す（Ｐ型）コネクタが取付けられる。また電力衛星２の
ケーブルの先端には大きなロート状のめず（１１１）コ
ネクタがそれぞれ取付けられる。このとき、両画Ｍ（ま
たは片方の衛Ｍ）に搭載されたビジコンカメラ５．５′
を使用して、地上局にて接続状況をモニターする。両画
星または片方の衛星に搭載されたガスジェット、電気推
進等のスラスタを地上からのコマンドにより制御し、術
産本体の軌道および姿勢を制御することによりコネクタ
を接近させ、ロート状のＪ型コネクタの中心部ＫＰ型コ
ネクタを接合する。A conical male (P type) connector is attached to the tip of the cable 3 of the mission satellite 1. Furthermore, large funnel-shaped socket (111) connectors are attached to the ends of the cables of the power satellites 2, respectively. At this time, the vidicon camera 5.5' mounted on both screens M (or one side M)
to monitor the connection status at the ground station. Gas jets, electric propulsion thrusters, etc. mounted on both satellites or one satellite are controlled by commands from the ground, and the orbit and attitude of the main body of the satellite are controlled to bring the connectors closer together, and the funnel-shaped J-shaped Connect the KP type connector at the center of the connector.
おす（Ｐ型）コネクタの先端部分には、強磁性体を取付
け、一方、めす（Ｊ型）コネクタの基端中心部にはコマ
ンドにてオン・オフ制御の可能な電磁石を取付ける電磁
石がオン状態のままコネクタを近づければ、両コネクタ
は磁力により確実に接続される。また反対に衛星の不具
合等により切離しが必要となった場合には、コマンドに
て電磁石をオフすることにより切離しが可能である。A ferromagnetic material is attached to the tip of the male (P type) connector, while an electromagnet that can be turned on and off by command is attached to the center of the base end of the female (J type) connector.The electromagnet is in the on state. If you bring the connectors close together, the two connectors will be securely connected by magnetic force. On the other hand, if it becomes necessary to disconnect due to a problem with the satellite, it can be done by turning off the electromagnet with a command.
第２図にコネクタの構造を示す。６はおす（Ｐ型）コネ
クタ、７はめず（Ｊ［）コネクタ、８は同心円上に導体
を巻いた端子帯、９は強磁性体または永久磁石、１０は
コマンドにてオン、拳オフ制御または電流反転制御可能
な電磁石である。Figure 2 shows the structure of the connector. 6 is a male (P type) connector, 7 is a female (J[) connector, 8 is a terminal strip with a conductor wound concentrically, 9 is a ferromagnetic material or permanent magnet, 10 is a command-on, fist-off control or It is an electromagnet that can control current reversal.
＾コネクタに＆ｉ接続時に一同位１１″′Ｃ−，接触す
るように、それぞれコーンを中心とした同心円上に導体
の端子帯８を備える。特におす（Ｐ型）コネクタの端子
帯は、接触面よりもわずかに突出させて弾性をもたせ接
触の確実化を図る。The terminal strips 8 of the conductor are provided on concentric circles with the cone as the center, so that the terminal strips 8 of the conductor are in contact with each other when connected to the connector.In particular, the terminal strips of the male (P type) connector are It is made to protrude slightly more than the 200 mm to give it elasticity and ensure contact.
おす（Ｐｉｌｌ＞コネクタ６の先端９に強磁性体を取付
けた場合には、めす（Ｊりコネクタ７の中心部にコマン
ドにてオン・オフ制御可能な電磁石を取付け、電磁石の
オン状態で接続を行い、切離す′ときＫは電磁石をオフ
にする。先端９に強磁性体の代りに永久磁石を用いる場
合には、電磁石ｌＯに電流方向の反転（すなわち極性の
反転）Ｉｌｊｌｌが可能な電磁石を用いることにより、
コネクタの接続および切離し一可能となる。If a ferromagnetic material is attached to the tip 9 of the male (Pill) connector 6, an electromagnet that can be turned on and off by command is attached to the center of the female (J) connector 7, and the connection is made when the electromagnet is on. When a permanent magnet is used instead of a ferromagnetic material at the tip 9, an electromagnet capable of reversing the current direction (that is, reversing the polarity) is used as the electromagnet lO. By using
It becomes possible to connect and disconnect the connector.
上記コイル状のケーブルは一方の衛星についてはこれを
省略し、コネクタを直接衛星本体に取付けることができ
る。The coiled cable described above can be omitted for one satellite, and the connector can be directly attached to the satellite body.
以上説明したよ５に、本発明によれｔｆ２１１の無人の
人工衛１を宇宙空間でケーブルにより接続することがで
きる。本発明によれば、同一規格のコネクタを備えた他
の衛星との相互接続も可能となさらに、衛星相互に接続
に限らず、宇宙ステーションと宇宙船との接続にも本発
明を実施することができる。As explained above, according to the present invention, the unmanned artificial guard 1 of TF211 can be connected by cable in outer space. According to the present invention, interconnection with other satellites equipped with connectors of the same standard is also possible.Furthermore, the present invention can be implemented not only for interconnection between satellites but also for connection between a space station and a spacecraft. I can do it.
第１図は本発明の実施例方式の構成図。
＄２図は接続コネクタの拡大図。
ｌ・・・ミッション衛１．２・・・電力衛星、３・・・
接続ケーブル、４・・・接続コネクタ、５・・・ビジコ
ンカメラ、６・・・Ｐ型コネクタ（おす）、７・・・Ｊ
ｌｌコネクタ（めす）、８・・・端子帯、９・・・強磁
性体または永久磁石、ｌＯ・・・オ／・オフ制御または
電流反転制御可能な電磁石。
特許出願人 日本電気株式台′社
Ｐｉ１図
出 ２図FIG. 1 is a block diagram of an embodiment of the present invention. Figure 2 is an enlarged view of the connector. l...Mission Satellite 1.2...Power satellite, 3...
Connection cable, 4...Connection connector, 5...Visicon camera, 6...P-type connector (male), 7...J
ll connector (female), 8... terminal strip, 9... ferromagnetic material or permanent magnet, lO... electromagnet capable of on/off control or current reversal control. Patent Applicant: NEC Corporation Pi1 Figure 2
Claims (1)
であってその外表面に複数の帯状の接続端子帯が形成さ
れ先端に磁性体が取付けられたおすコネクタとを備え、 他方の人工衛星Ｋ、 内表面が上記おすコネクタに合致する円錐形状でありそ
の内表面に上記端子帯に整合する端子帯が形成されその
基端に電磁石が取付けられためすコネクタとｔｉｉｉえ
、 上記人工衛星の少なくとも一方に搭載され上記嫉綬ケー
ブルの状態の影像を撮影して地上に送信する手段を備え
、 この手段の送信信号を地上で監視しながら上記人工衛星
の少なくとも一方の姿勢および位置を遠隔制御すること
により上記おすコネクタとめずコネクタとを接続させる
ことを特徴とする人工衛星の接続方式。(1) One of the satellites has a coil-shaped connection cable attached to the tip of the connection cable, the outer surface of which has a circular stitch shape, and a plurality of strip-shaped connection terminal strips formed on the outer surface, and a magnetic terminal at the tip. The other artificial satellite K has a conical inner surface that matches the male connector, a terminal strip matching the terminal strip is formed on the inner surface, and an electromagnet is attached to the base end of the conical inner surface. a female connector attached to the satellite; A method for connecting an artificial satellite, characterized in that the male connector and the male connector are connected by remotely controlling the attitude and position of at least one of the artificial satellites.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP57025176A JPS58142000A (en) | 1982-02-17 | 1982-02-17 | Connection system of artificial satellite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP57025176A JPS58142000A (en) | 1982-02-17 | 1982-02-17 | Connection system of artificial satellite |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS58142000A true JPS58142000A (en) | 1983-08-23 |
| JPS6148480B2 JPS6148480B2 (en) | 1986-10-24 |
Family
ID=12158692
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP57025176A Granted JPS58142000A (en) | 1982-02-17 | 1982-02-17 | Connection system of artificial satellite |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS58142000A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS61268599A (en) * | 1985-03-20 | 1986-11-28 | スペ−ス・インダストリ−ズ・インコ−ポレ−テツド | Module type space craft system and assembly method thereof |
| JP2011162183A (en) * | 2010-02-10 | 2011-08-25 | Astrium Gmbh | Towing device for towing space navigation machine on orbit, space navigation machine and towing space navigation machine |
| WO2021059134A1 (en) | 2019-09-24 | 2021-04-01 | Astroscale Israel Ltd. | In-orbit spacecraft servicing through umbilical connectors |
| WO2022080208A1 (en) * | 2020-10-16 | 2022-04-21 | 株式会社アストロスケール | Space navigating body and capture system |
| WO2023149386A1 (en) * | 2022-02-01 | 2023-08-10 | ＳｋｙＤｅｅｒ株式会社 | Satellite control method |
| JP2023112528A (en) * | 2022-02-01 | 2023-08-14 | ＳｋｙＤｅｅｒ株式会社 | Satellite control method |
-
1982
- 1982-02-17 JP JP57025176A patent/JPS58142000A/en active Granted
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS61268599A (en) * | 1985-03-20 | 1986-11-28 | スペ−ス・インダストリ−ズ・インコ−ポレ−テツド | Module type space craft system and assembly method thereof |
| JPH0729640B2 (en) * | 1985-03-20 | 1995-04-05 | スペ−ス・インダストリ−ズ・インコ−ポレ−テツド | Modular spacecraft system |
| JP2011162183A (en) * | 2010-02-10 | 2011-08-25 | Astrium Gmbh | Towing device for towing space navigation machine on orbit, space navigation machine and towing space navigation machine |
| WO2021059134A1 (en) | 2019-09-24 | 2021-04-01 | Astroscale Israel Ltd. | In-orbit spacecraft servicing through umbilical connectors |
| EP4034465A4 (en) * | 2019-09-24 | 2023-09-27 | Astroscale Israel Ltd. | In-orbit spacecraft servicing through umbilical connectors |
| WO2022080208A1 (en) * | 2020-10-16 | 2022-04-21 | 株式会社アストロスケール | Space navigating body and capture system |
| WO2023149386A1 (en) * | 2022-02-01 | 2023-08-10 | ＳｋｙＤｅｅｒ株式会社 | Satellite control method |
| JP2023112528A (en) * | 2022-02-01 | 2023-08-14 | ＳｋｙＤｅｅｒ株式会社 | Satellite control method |
Also Published As
| Publication number | Publication date |
|---|---|
| JPS6148480B2 (en) | 1986-10-24 |
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