JPH08244697A - Orbit work system - Google Patents
Orbit work systemInfo
- Publication number
- JPH08244697A JPH08244697A JP7048388A JP4838895A JPH08244697A JP H08244697 A JPH08244697 A JP H08244697A JP 7048388 A JP7048388 A JP 7048388A JP 4838895 A JP4838895 A JP 4838895A JP H08244697 A JPH08244697 A JP H08244697A
- Authority
- JP
- Japan
- Prior art keywords
- orbit
- holding
- main body
- working machine
- arrangement surface
- 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
- 238000002347 injection Methods 0.000 claims description 15
- 239000007924 injection Substances 0.000 claims description 15
- 238000010586 diagram Methods 0.000 description 4
- 238000011109 contamination Methods 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 238000007689 inspection Methods 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 239000003380 propellant Substances 0.000 description 2
- 238000004891 communication Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000002093 peripheral effect Effects 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
- B64G1/641—Interstage or payload connectors
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Manipulator (AREA)
Abstract
Description
【０００１】[0001]
【産業上の利用分野】この発明は、例えば静止軌道等に
打上げられる通信衛星、放送衛星等の人工衛星を含む宇
宙航行体の部品交換や保守点検等を行うのに好適する軌
道上作業システムに関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an on-orbit working system suitable for parts replacement and maintenance and inspection of spacecraft including artificial satellites such as communication satellites and broadcasting satellites launched into geostationary orbit. .
【０００２】[0002]
【従来の技術】周知のように、人工衛星等の宇宙航行体
においては、所定のミッションを実現するために、電子
機器や宇宙構造物等の各種の宇宙搭載機器が搭載され、
宇宙空間に打上げられた後、これら宇宙搭載機器を運用
可能状態に設定して、所望の運用が実行される。2. Description of the Related Art As is well known, in a spacecraft such as an artificial satellite, various space-mounted devices such as electronic devices and space structures are mounted to realize a predetermined mission.
After being launched into outer space, these space-equipped devices are set to an operable state and desired operation is executed.
【０００３】ところで、最近の宇宙開発の分野において
は、宇宙空間に打上げた宇宙航行体の長寿命化を図る手
段として、マニピュレータシステムを搭載した軌道上作
業機を用いて宇宙空間に配置された宇宙航行体の分品交
換や修理を含む保守点検を実行する軌道上作業システム
を構築する構想がある。このような軌道上作業システム
としては、宇宙ステーション等の大形の宇宙航行体に軌
道上作業機を係留する如く配置して、この軌道上作業機
を宇宙航行体から必要に応じて射出し、該軌道上作業機
が自力で作業用宇宙航行体まで飛翔して所望の作業メニ
ューを実行するように構成される。この軌道上作業機を
宇宙航行体から射出する射出手段としては、推進機、例
えばスラスタの推進力を利用したり、あるいはカタパル
トと称する射出機構を用いて構成することが考えられて
いる。By the way, in the field of recent space development, as a means for extending the life of a spacecraft launched into outer space, a space arranged in outer space using an on-orbit working machine equipped with a manipulator system. There is a plan to build an on-orbit work system that carries out maintenance inspections including replacement and repair of navigation parts. As such an on-orbit working system, a large spacecraft such as a space station is arranged so as to moor the orbital working machine, and the orbiting working machine is ejected from the spacecraft as necessary. The on-orbit work machine is configured to fly to a work spacecraft by itself and execute a desired work menu. As an injection means for ejecting the on-orbit working machine from the spacecraft, it is considered that the propulsion machine, for example, thruster is used, or an injection mechanism called a catapult is used.
【０００４】しかしながら、上記射出手段では、前者の
場合、スラスタからのスラスタプルームが発生すること
で、射出の度ごとにスラスタプルームによる汚染が発生
するために、その対策が必要となり、面倒であるという
問題を有する。また、後者の場合にあっては、射出時の
軌道上作業機に与える初速度を十分に採るように構成す
ると、その構造が非常に複雑となり、大形となるという
問題を有する。係る事情は、軌道上作業システムを構築
するのに重要な課題の一つとなっている。In the former case, however, in the former case, a thruster plume is generated from the thruster, which causes contamination by the thruster plume each time it is ejected. Therefore, it is necessary to take measures against it, which is troublesome. Have a problem. In the latter case, if the initial velocity given to the on-orbit working machine at the time of injection is sufficiently configured, the structure becomes very complicated and large. This situation is one of the important issues in constructing an on-orbit work system.
【０００５】[0005]
【発明が解決しようとする課題】以上述べたように、軌
道上作業システムにあっては、軌道上作業機を射出する
射出手段として、汚染が問題となったり、あるいは構造
が複雑で、大形となるという問題を有する。As described above, in the on-orbit working system, contamination is a problem as the injection means for injecting the on-orbit working machine, or the structure is complicated and large in size. There is a problem that
【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、軌道上作業機射出動作を高精度
に実現し得るようにした軌道上作業システムを提供する
ことを目的とする。The present invention has been made in view of the above circumstances, and an object thereof is to provide an on-orbit working system having a simple structure and capable of highly accurately performing an on-orbit working machine injection operation. .
【０００７】[0007]
【課題を解決するための手段】この発明の軌道上作業シ
ステムは、推力発生部を駆動して自力で飛翔する作業機
構部が搭載された複数の軌道上作業機と、この軌道上作
業機が搭載される配置面を有した本体部が、前記配置面
に対して略直交する軸回りに回転駆動されるスピン安定
型姿勢制御方式の宇宙航行体と、前記本体部の配置面に
前記軌道上作業機を解放自在に位置決め保持する保持解
放手段とを備え、前記軌道上作業機は、前記保持解放手
段による保持が解放されると、前記本体部の回転駆動に
ともなう角運動量により宇宙空間に射出するように構成
したものである。SUMMARY OF THE INVENTION An on-orbit working system of the present invention comprises a plurality of on-orbit working machines equipped with a working mechanism section for driving a thrust generating section to fly by itself, and the on-orbit working machines. A main body having an arrangement surface to be mounted is spin-stable attitude control type spacecraft that is rotationally driven around an axis substantially orthogonal to the arrangement surface, and the main body is arranged on the orbit on the arrangement surface. Holding or releasing means for positioning and holding the working machine in a releasable manner, and when the holding by the holding and releasing means is released, the on-orbit working machine is ejected to outer space due to the angular momentum accompanying the rotational drive of the main body section. It is configured to do.
【０００８】[0008]
【作用】上記構成によれば、軌道上作業機は、保持解放
手段を介して宇宙航行体の本体部の配置面に搭載され、
宇宙航行体の回転に伴う角運動量が付与され、保持解放
手段による保持が解放されると、その角運動量により宇
宙空間に射出される。これにより、汚染原因となる推薬
を備えた射出用の推力発生機構や複雑な構造の射出機構
等の射出手段を付加することなく、安定した高精度な射
出動作が可能となる。According to the above construction, the on-orbit working machine is mounted on the arrangement surface of the main body of the spacecraft through the holding and releasing means,
When the angular momentum associated with the rotation of the spacecraft is given and the holding by the holding / releasing means is released, it is ejected into outer space by the angular momentum. As a result, a stable and highly accurate injection operation can be performed without adding an injection means such as a thrust generation mechanism for injection having a propellant that causes contamination or an injection mechanism having a complicated structure.
【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。図１は、この発明の一実施例に
係る軌道上作業システムを示すもので、１０は、母船を
構成する宇宙航行体で、周知のスピン安定型の姿勢制御
方式に構成される。この宇宙航行体１０は、本体部１０
ａが例えば円錐形状に形成され、その回転方向と直交す
る一方面には、作業機搭載用の配置面１１が設けられ
る。この配置面１１には、複数の保持解放機構部１２
（図中では、図の都合上、一箇所のみ図示）が所定の間
隔を有して放射状に設けられる。そして、この保持解放
機構部１２には、軌道上作業機１３がそれぞれ解放自在
に保持されて搭載される。軌道上作業機１３には、マニ
ピュレータを含む作業機構部が設けられる。Embodiments of the present invention will be described below in detail with reference to the drawings. FIG. 1 shows an on-orbit working system according to an embodiment of the present invention. Reference numeral 10 denotes a spacecraft constituting a mother ship, which is constructed in a well-known spin-stable attitude control system. The spacecraft 10 includes a main body 10
a is formed in a conical shape, for example, and a working machine mounting arrangement surface 11 is provided on one surface thereof that is orthogonal to the rotation direction thereof. A plurality of holding and releasing mechanism parts 12 are provided on the placement surface 11.
(In the figure, only one location is shown for the sake of convenience of the figure) and are provided radially with a predetermined interval. The orbital work machines 13 are releasably held and mounted on the holding / releasing mechanism section 12. The on-orbit working machine 13 is provided with a working mechanism section including a manipulator.
【００１０】本体部１０ａには、送受信アンテナ１４が
設けられ、この送受信アンテナ１４には、例えば地上局
からの作業指令信号が受信される。そして、本体部１０
ａの周壁部には、太陽電池パネル１５が設けられる。A transmission / reception antenna 14 is provided in the main body 10a, and the transmission / reception antenna 14 receives a work command signal from a ground station, for example. And the main body 10
The solar cell panel 15 is provided on the peripheral wall portion of a.
【００１１】上記軌道上作業機１３には、自力飛翔用推
進発生部１３ａが搭載されると共に、各種の作業機能を
持つマニピュレータを含む作業機構部１３ｂが搭載され
る。上記構成において、宇宙航行体１０は、その本体部
１０ａが回転駆動され、その回転力により、姿勢が制御
されて宇宙空間を飛翔する。そして、送受信アンテナ１
４に作業指令信号が入力されると、図示しない指令制御
部が作業メニューに対応した軌道上作業機１３を選択
し、その保持解放機構１２を例えば図示しない被作業用
宇宙航行体に対応した状態で駆動制御して、その保持を
解放する。すると、軌道上作業機１３は、宇宙航行体１
０の本体部１０ａの回転に伴う角運動量により、宇宙空
間に射出される。ここで、軌道上作業機１３は、その推
進発生部１３ａが駆動され、自力で被作業用宇宙航行体
（図示せず）に接近して、その作業機構部１３ｂを駆動
制御して要求される作業メニューを実行する。The on-orbit working machine 13 is equipped with a self-propelled flight propulsion generator 13a and a working mechanism 13b including a manipulator having various working functions. In the above structure, the body 10a of the spacecraft 10 is rotatably driven, and its rotational force causes the attitude thereof to be controlled to fly in outer space. Then, the transmitting / receiving antenna 1
When a work command signal is input to 4, the command control unit (not shown) selects the on-orbit working machine 13 corresponding to the work menu, and the holding / releasing mechanism 12 corresponds to, for example, a not-shown spacecraft for working. The drive is controlled by and the hold is released. Then, the on-orbit working machine 13 moves to the spacecraft 1
It is injected into outer space due to the angular momentum associated with the rotation of the main body 10a of zero. Here, the on-orbit working machine 13 is requested by driving its propulsion generating section 13a, approaching the work spacecraft (not shown) by itself, and drivingly controlling its working mechanism section 13b. Execute the work menu.
【００１２】また、作業が完了した軌道上作業機１３
は、その推進発生部１３ａを駆動して自力で宇宙航行体
１０に帰還して、初期の保持解放機構部１２に係留され
る如く保持されて本体部１０の配置面１１に位置決めさ
れて保持される。この際、宇宙航行体１０は、例えば本
体部１０ａの回転の駆動が停止され、三軸姿勢制御状態
に切り替えられて保持動作が実行され、保持後、再びス
ピン安定型の姿勢制御に切り替え設定される。Further, the on-orbit working machine 13 which has completed the work
Drives the propulsion generation unit 13a to return to the spacecraft 10 by itself, and is held so as to be moored by the initial holding / releasing mechanism unit 12 and positioned and held on the arrangement surface 11 of the main body unit 10. It At this time, in the spacecraft 10, for example, the driving of rotation of the main body 10a is stopped, the holding operation is executed by switching to the three-axis attitude control state, and after the holding operation, the setting is switched to the spin stable attitude control again. It
【００１３】このように、上記軌道上作業システムは、
複数の保持解放機構部１２を宇宙航行体１０の本体部１
０ａの配置面１１に放射状に設け、軌道上作業機１３を
保持解放機構部１２を解放自在に位置決め保持して、こ
の保持解放機構部１２の解放動作に連動して、本体部１
０ａの回転駆動に伴う角運動量を利用して軌道上作業機
１３を宇宙空間に射出するように構成した。これによれ
ば、汚染原因となる推薬を備えた射出用の推力発生機構
や複雑な構造の射出機構等の射出手段を付加することな
く、簡単な構成で、安定した高精度な射出動作が実現さ
れる。As described above, the above-mentioned orbital work system is
The plurality of holding and releasing mechanism parts 12 are connected to the body part 1 of the spacecraft 10.
0a is arranged on the arrangement surface 11 in a radial manner, the on-orbit working machine 13 is repositionably held by the holding and releasing mechanism section 12, and the main body section 1 is interlocked with the releasing operation of the holding and releasing mechanism section 12.
The on-orbit working machine 13 is configured to be ejected into outer space by utilizing the angular momentum associated with the rotational drive of 0a. According to this, a stable and highly accurate injection operation can be performed with a simple configuration without adding an injection means such as a thrust generation mechanism for injection equipped with a propellant that causes pollution or an injection mechanism having a complicated structure. Will be realized.
【００１４】なお、この発明は、上記実施例に限ること
なく、図２乃至図４に示すように構成される。但し、こ
こでは、図中において、前記図１と同一部分について
は、同一符号を付して、その説明を省略する。The present invention is not limited to the above embodiment, but is constructed as shown in FIGS. However, in this figure, the same parts as those in FIG. 1 are designated by the same reference numerals, and the description thereof will be omitted.
【００１５】図２は、宇宙航行体１０の本体部１０ａの
配置面１１に対して矢印Ａ，Ｂ方向に伸縮自在な複数の
案内レール２０を所定の間隔を有して放射状に設け、こ
の案内レール２０には、それぞれ軌道上作業機１３を保
持解放機構部１２（図２中では、図の都合上、図示せ
ず）を介して解放自在に位置決め保持するように構成し
たものである。In FIG. 2, a plurality of guide rails 20 that are extendable and contractible in the directions of arrows A and B are radially provided at predetermined intervals with respect to the arrangement surface 11 of the body 10a of the spacecraft 10, and the guide Each of the rails 20 is configured to releasably position and hold the on-orbit working machine 13 via a holding / releasing mechanism section 12 (not shown in FIG. 2 for convenience of illustration).
【００１６】上記構成において、軌道上作業機１３を射
出する場合には、先ず、所望の案内レール２０を宇宙空
間に向けて伸張させた後、その保持解放機構部１２を制
御して軌道上作業機１３の保持を解放する。すると、軌
道上作業機１３は、宇宙航行体１０の本体部１０ａの回
転に伴う角運動量により、案内レール２０に案内されて
宇宙空間の所望の方向に射出される。In the above structure, when the on-orbit working machine 13 is ejected, first, the desired guide rail 20 is extended toward outer space, and then the holding / releasing mechanism section 12 is controlled to perform the on-orbit working. Release holding of machine 13. Then, the on-orbit working machine 13 is guided by the guide rail 20 and ejected in a desired direction in outer space due to the angular momentum associated with the rotation of the main body 10a of the spacecraft 10.
【００１７】また、図３は、宇宙航行体１０の本体部１
０ａの配置面１１に設ける保持解放機構部１２を位置調
整機構２１を介して、回転軸回りに移動自在に配設し、
この位置調整機構２１を介して保持解放機構部１２を移
動調整することにより、軌道上作業機１３の配置位置を
可変設定するように構成したものである。Further, FIG. 3 shows the main body 1 of the spacecraft 10.
The holding / releasing mechanism portion 12 provided on the arrangement surface 11 of 0a is disposed movably around the rotation axis via the position adjusting mechanism 21.
The holding / releasing mechanism section 12 is moved and adjusted via the position adjusting mechanism 21 to variably set the arrangement position of the on-orbit working machine 13.
【００１８】上記構成において、宇宙航行体１０の本体
部１１ａの回転に伴う角運動量を利用して軌道上作業機
１３の一台が宇宙空間に射出された状態で、残りの軌道
上作業機１３を保持する保持解放機構部１２を位置調整
機構２１を介して移動して配置調整し、宇宙港構体１０
の本体部１０ａのバランスを採る。これにより、複数の
軌道上作業機１３を宇宙空間に射出した状態において、
宇宙航行体１０の本体部１０ａの安定した姿勢制御が実
現される。In the above structure, one of the on-orbit working machines 13 is ejected into outer space by utilizing the angular momentum associated with the rotation of the main body 11a of the spacecraft 10, and the remaining on-orbit working machines 13 are discharged. The holding / releasing mechanism section 12 for holding the
The balance of the main body part 10a is taken. As a result, in a state where the plurality of orbital working machines 13 are ejected into outer space,
Stable attitude control of the body 10a of the spacecraft 10 is realized.
【００１９】さらに、図４は、母船を構成する宇宙航行
体３０として複数、例えば第１及び第２の本体部３１，
３２を支持構体３３を介して分離させて回転駆動自在に
配設し、この第１及び第２の本体部３１，３２にそれぞ
れ配置面３１ａ，３２ａを設けて軌道上作業機１３を保
持解放機構部１２（図４中では、図の都合上、図示せ
ず）を介して解放自在に配設するように構成したもので
ある。Further, FIG. 4 shows a plurality of space navigation bodies 30 constituting the mother ship, for example, first and second main body portions 31,
32 are separated via a support structure 33 so as to be rotatably driven, and the first and second main body portions 31 and 32 are provided with disposition surfaces 31a and 32a, respectively, to hold and release the on-orbit working machine 13. It is configured to be releasably arranged via a portion 12 (not shown in FIG. 4 for convenience of illustration).
【００２０】なお、上記第１及び第２の本体部３１，３
２においては、例えば前記図２に示す案内レール２０を
設けたり、あるいは前記図３に示す位置調整機構２１を
組合わせて配設して、同様に軌道上作業機１３を搭載す
るように構成することも可能である。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
論のことである。The first and second main body portions 31 and 3 are
2, the guide rail 20 shown in FIG. 2 is provided, or the position adjusting mechanism 21 shown in FIG. 3 is provided in combination, and the on-orbit working machine 13 is similarly mounted. It is also possible. Therefore, it is needless to say that the present invention is not limited to the above-described embodiment, and that various modifications can be made without departing from the scope of the present invention.
【００２１】[0021]
【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、軌道上作業機射出動作を高精度に
実現し得るようにした軌道上作業システムを提供するこ
とができる。As described above in detail, according to the present invention, it is possible to provide an on-orbit working system having a simple structure and capable of highly accurately performing the on-orbit working machine injection operation.
【図面の簡単な説明】[Brief description of drawings]
【図１】この発明の一実施例に係る軌道上作業システム
を示した図。FIG. 1 is a diagram showing an on-orbit working system according to an embodiment of the present invention.
【図２】この発明の他の実施例を示した図。FIG. 2 is a diagram showing another embodiment of the present invention.
【図３】この発明の他の実施例を示した図。FIG. 3 is a diagram showing another embodiment of the present invention.
【図４】この発明の他の実施例を示した図。FIG. 4 is a diagram showing another embodiment of the present invention.
１０…宇宙航行体。 １０ａ…本体部。 １１，３１ａ，３２ａ…配置面。 １２…保持解放機構部。 １３…軌道上作業機。 １３ａ…推進発生部。 １３ｂ…作業機構部。 １４…送受信アンテナ。 １５…太陽電池パネル。 ２０…案内レール。 ２１…位置調整機構。 ３３…支持構体。 10 ... Spacecraft. 10a ... main body part. 11, 31a, 32a ... Arrangement surface. 12 ... Holding / release mechanism section. 13 ... Orbital work machine. 13a ... Propulsion generation unit. 13b ... Working mechanism section. 14 ... Transmitting / receiving antenna. 15. Solar panel. 20 ... Guide rail. 21 ... Position adjustment mechanism. 33 ... Support structure.
Claims (4)
業機構部が搭載された複数の軌道上作業機と、 この軌道上作業機が搭載される配置面を有した本体部
が、前記配置面に対して略直交する軸回りに回転駆動さ
れるスピン安定型姿勢制御方式の宇宙航行体と、 前記本体部の配置面に前記軌道上作業機を解放自在に位
置決め保持する保持解放手段とを具備し、前記軌道上作
業機は、前記保持解放手段による保持が解放されると、
前記本体部の回転駆動にともなう角運動量により宇宙空
間に射出されることを特徴とする軌道上作業システム。1. A plurality of on-orbit working machines having a working mechanism section for driving a thrust generating section to fly by itself, and a main body section having an arrangement surface on which the on-orbit working machines are mounted, A space navigation body of a spin stable attitude control system that is rotationally driven about an axis that is substantially orthogonal to the arrangement surface; and holding and releasing means that releasably positions and holds the on-orbit working machine on the arrangement surface of the main body. When the holding by the holding and releasing means is released, the on-orbit working machine,
An on-orbit working system characterized by being ejected into outer space by the angular momentum associated with the rotational drive of the main body.
業機構部が搭載された複数の軌道上作業機と、 この軌道上作業機が搭載される配置面を有した本体部
が、前記配置面に対して略直交する軸回りに回転駆動さ
れるスピン安定型姿勢制御方式の宇宙航行体と、 前記本体部の配置面に回転方向と直交する方向に伸縮自
在に設けられ、前記軌道上作業機が射出自在に係合され
る案内レールを有し、該案内レールを伸縮駆動して、前
記軌道上作業機の射出方向を設定する射出方向設定手段
と、 前記宇宙航行体の案内レールに前記軌道上作業機を解放
自在に位置決め保持する保持解放手段とを具備し、前記
軌道上作業機は、前記保持解放手段による保持が解放さ
れると、前記案内レールに案内されて前記本体部の回転
駆動にともなう角運動量により宇宙空間に射出されるこ
とを特徴とする軌道上作業システム。2. A plurality of on-orbit working machines equipped with a working mechanism section for driving a thrust generating section to fly by itself, and a main body section having an arrangement surface on which the on-orbit working machines are mounted, A space navigation body of a spin-stable attitude control system that is driven to rotate about an axis that is substantially orthogonal to the arrangement surface, and is provided on the arrangement surface of the main body portion so as to be extendable and contractible in a direction orthogonal to the rotation direction. The working machine has a guide rail engageable in an injectable manner, and the guide rail is extended / contracted to set the injection direction of the working machine in orbit, and the guide rail of the spacecraft. Holding release means for releasably positioning and holding the on-orbit working machine, the on-orbit working machine being guided by the guide rail when the holding by the holding and releasing means is released, Depending on the angular momentum associated with rotation drive An on-orbit work system characterized by being injected into outer space.
業機構部が搭載された複数の軌道上作業機と、 この軌道上作業機が搭載される配置面を有した本体部
が、前記配置面に対して略直交する軸回りに回転駆動さ
れるスピン安定型姿勢制御方式の宇宙航行体と、 前記本体部の配置面に前記軌道上作業機を解放自在に位
置決め保持する保持解放手段と、 この保持解放手段を前記本体部の配置面の回転方向に移
動して前記軌道上作業機の保持位置を可変設定する位置
調整手段とを具備し、前記軌道上作業機は、前記保持解
放手段による保持が解放されると、前記本体部の回転駆
動にともなう角運動量により宇宙空間に射出され、この
状態で前記位置調整手段が前記保持解放手段の位置を設
定して前記軌道上作業機の配置面上の位置を設定するこ
とを特徴とする軌道上作業システム。3. A plurality of on-orbit working machines equipped with a working mechanism section for driving a thrust generating section to fly by itself, and a main body section having an arrangement surface on which the on-orbit working machines are mounted, A space navigation body of a spin stable attitude control system that is rotationally driven about an axis that is substantially orthogonal to the arrangement surface; and holding and releasing means that releasably positions and holds the on-orbit working machine on the arrangement surface of the main body. And a position adjusting means for variably setting a holding position of the on-orbit working machine by moving the holding / releasing means in a rotation direction of a disposition surface of the main body section, and the on-orbit working machine includes the holding / releasing means. When the holding by is released into the outer space due to the angular momentum accompanying the rotational drive of the main body, the position adjusting means sets the position of the holding and releasing means in this state to arrange the on-orbit working machine. Setting the position on the surface On-orbit work system characterized by.
複数の本体部が分離配置されることを特徴とする請求項
１乃至４のいずれか一つ記載の軌道作業システム。4. The orbital work system according to claim 1, wherein the spacecraft has a plurality of main bodies having the arrangement surface arranged separately.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP7048388A JPH08244697A (en) | 1995-03-08 | 1995-03-08 | Orbit work system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP7048388A JPH08244697A (en) | 1995-03-08 | 1995-03-08 | Orbit work system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH08244697A true JPH08244697A (en) | 1996-09-24 |
Family
ID=12801925
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP7048388A Pending JPH08244697A (en) | 1995-03-08 | 1995-03-08 | Orbit work system |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH08244697A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005075209A (en) * | 2003-09-02 | 2005-03-24 | Kawasaki Heavy Ind Ltd | Separation structure of artificial satellite, and rocket |
| CN105151329A (en) * | 2015-09-02 | 2015-12-16 | 李新洪 | Interface device and adapting method and system of on-orbit replaceable module carrying adapter |
| WO2022153619A1 (en) * | 2021-01-15 | 2022-07-21 | Astroscale Holdings Inc. | Method and system for multi-object space debris removal |
-
1995
- 1995-03-08 JP JP7048388A patent/JPH08244697A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005075209A (en) * | 2003-09-02 | 2005-03-24 | Kawasaki Heavy Ind Ltd | Separation structure of artificial satellite, and rocket |
| CN105151329A (en) * | 2015-09-02 | 2015-12-16 | 李新洪 | Interface device and adapting method and system of on-orbit replaceable module carrying adapter |
| WO2022153619A1 (en) * | 2021-01-15 | 2022-07-21 | Astroscale Holdings Inc. | Method and system for multi-object space debris removal |
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