JPH0288400A - Docking device - Google Patents
Docking deviceInfo
- Publication number
- JPH0288400A JPH0288400A JP63238947A JP23894788A JPH0288400A JP H0288400 A JPH0288400 A JP H0288400A JP 63238947 A JP63238947 A JP 63238947A JP 23894788 A JP23894788 A JP 23894788A JP H0288400 A JPH0288400 A JP H0288400A
- Authority
- JP
- Japan
- Prior art keywords
- side coupling
- levers
- rod
- docking
- shaft
- 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
- 238000003032 molecular docking Methods 0.000 title claims abstract description 24
- 230000008878 coupling Effects 0.000 claims abstract description 49
- 238000010168 coupling process Methods 0.000 claims abstract description 49
- 238000005859 coupling reaction Methods 0.000 claims abstract description 49
- 230000007246 mechanism Effects 0.000 claims abstract description 13
- 238000010586 diagram Methods 0.000 description 5
- 238000005516 engineering process Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000013011 mating 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
- B64G1/646—Docking or rendezvous systems
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Holders For Apparel And Elements Relating To Apparel (AREA)
Abstract
Description
【発明の詳細な説明】
〔産業上の利用分計〕
本発明は運動体同士の結合に用いられるドツキング装置
に関し、特に宇宙空間で行われる人工衛星(有人宇宙船
)の燃料補給、材料実験の試料回収、故障機器の交換修
理等のサービスを行う場合に必要となる人工衛星同士あ
るいは人工衛星と宇宙基地との機械的な結合及び離脱の
ためのドツキング装置に関する。[Detailed Description of the Invention] [Industrial Applications] The present invention relates to a docking device used for coupling moving bodies together, and is particularly useful for refueling artificial satellites (manned spacecraft) and material experiments conducted in outer space. This invention relates to a docking device for mechanical coupling and detachment between artificial satellites or between an artificial satellite and a space base, which is necessary for services such as sample collection, replacement and repair of malfunctioning equipment, etc.
第4図は従来のドツキング装置を示すもので。 Figure 4 shows a conventional docking device.
21は能動側結合盤であり、ラッチ機構22〜25を有
する。26は受動側結合盤であり、ラッチ受機構27〜
30を有する。能動側結合盤21及び受動側結合盤26
は1人工衛星又は宇宙基地の端部に取付けられ1人工衛
星と人工衛星又は人工衛星と宇宙基地とを結合するとき
は能動側結合盤21と受動側結合盤26を接近させラッ
チ機構22〜25をそれぞれ、ラッチ受機構27〜30
に接触させ、ラッチングする。21 is an active side coupling board, which has latch mechanisms 22-25. 26 is a passive side coupling board, and latch receiving mechanism 27~
It has 30. Active side coupling board 21 and passive side coupling board 26
is attached to the edge of one artificial satellite or space base, and when connecting one artificial satellite to an artificial satellite or an artificial satellite to a space base, the active side coupling board 21 and the passive side coupling board 26 are brought close to each other, and the latch mechanism 22 to 25 respectively, the latch receiving mechanisms 27 to 30
contact and latch.
また、離脱するときは、これら4箇所のラッチを解除し
、能動側結合盤21と受動側結合盤26を弓離す。Further, when detaching, release the latches at these four locations and separate the active side coupling board 21 and the passive side coupling board 26.
上述した従来のドツキング装置は、ラッチ機構が複雑で
信頼性に欠けるという欠点があった。The above-described conventional docking device has the disadvantage that the latching mechanism is complicated and lacks reliability.
又、結合する際、能動側結合盤と受動側結合盤との中心
合わせ及びラッチ機構とう、チ受機構との位置合わせが
必要になり、操作上特別な注意を要すると(・う欠点が
あった。In addition, when joining, it is necessary to center the active-side joining board and the passive-side joining board, and to align the latch mechanism and the catch mechanism, which requires special care in operation. Ta.
本発明の課題は、運動体同士、特に軌道上における人工
衛星同士あるいは人工衛星と宇宙基地との結合及び離脱
を高い信頼性でしかも容易な操作で行えるドツキング装
置を提供することにある。SUMMARY OF THE INVENTION An object of the present invention is to provide a docking device that can connect and detach moving bodies, particularly between artificial satellites in orbit, or between an artificial satellite and a space base with high reliability and easy operation.
本発明は、ドツキングする側の運動体に能動側結合盤を
設け、該能動側結合盤は、その中心部に盤面に対して垂
直な方向に延び、かつ軸方向運動あるいは回転運動可能
な軸と、該軸の軸方向運動あるいは回転運動によりかさ
状に開閉するレバーとを有し、前記ドツキングする側の
運動体には更に、前記軸を軸方向運動あるいは回転運動
させる機構を設け、ドツキングされる側の運動体の結合
部には前記軸と閉じた状態の前記レバーとが挿通可能な
穴を設けて成るドツキング装置である。In the present invention, an active coupling plate is provided on the moving body on the docking side, and the active coupling plate has a shaft at its center that extends in a direction perpendicular to the plate surface and is capable of axial movement or rotational movement. , a lever that opens and closes in an umbrella shape by axial movement or rotational movement of the shaft, and the movable body on the docking side is further provided with a mechanism for axial movement or rotational movement of the shaft, so that the shaft is docked. This is a docking device in which a hole through which the shaft and the lever in a closed state can be inserted is provided in the connecting portion of the side moving body.
第1図、第2図は本発明の第1の実施例を示す。 1 and 2 show a first embodiment of the present invention.
本実施例のドツキング装置は、中心部に、軸方向に往復
運動して複数のレバー2〜4.5〜7による結合機構を
動作させるロッド(軸)9を有し9周辺部には受動側結
合盤とのかん合のためのテーパ14を有する能動側結合
盤1と。The docking device of this embodiment has a rod (shaft) 9 in the center that reciprocates in the axial direction to operate a coupling mechanism made up of a plurality of levers 2 to 4, and 5 to 7. an active coupling plate 1 having a taper 14 for mating with the coupling plate;
中心部に円形の穴16を有し、能動側結合盤1と対向す
る側の周辺部には能動側結合盤13とのかん合のための
テーパ15を有する受動側結合盤13と、歯車10.ウ
オーム歯車11及びモータ12を含んでロッド9を軸方
向に運動させる駆動機構とから構成される。A passive side coupling plate 13 having a circular hole 16 in the center and a taper 15 on the side opposite to the active side coupling plate 1 for engagement with the active side coupling plate 13, and a gear 10. .. The drive mechanism includes a worm gear 11 and a motor 12 to move the rod 9 in the axial direction.
第1図はドツキング前・に能動側結合盤1と受動側結合
盤13とが接近した状態を示す。能動側結合盤1の中心
部をロッド9が盤面に対して垂直に貫通しており、ロッ
ド9にはレバー2゜6.4の一端がビン結合されている
。テーパ14は受動側結合盤13のテーパ部15とのか
ん合を容易にするためのものである。レバー2,3゜4
の他端はレバー5.6.7の一端とビン結合され、レバ
ー5,6.7の他端は口、ド9の端部8とビン結合され
ている。口、ド9には歯91が形成され、この歯91と
歯車10はラック・ピニオン結合され、歯車10は更に
、モータ12の回転軸に取付けられたウオーム歯車11
と結合されている。このような駆動機構により。FIG. 1 shows a state in which the active side coupling board 1 and the passive side coupling board 13 are close to each other before docking. A rod 9 passes through the center of the active side coupling board 1 perpendicularly to the board surface, and one end of a lever 2°6.4 is connected to the rod 9 via a pin. The taper 14 is for facilitating engagement with the tapered portion 15 of the passive coupling board 13. Lever 2,3゜4
The other end is connected to one end of the lever 5,6.7, and the other end of the lever 5,6.7 is connected to the end 8 of the door 9. Teeth 91 are formed on the mouth and door 9, and the teeth 91 and the gear 10 are connected to each other by a rack and pinion.
is combined with With such a drive mechanism.
モータ12の駆動によってロッド9が図中左右。Driven by the motor 12, the rod 9 moves left and right in the figure.
すなわち軸方向に動く。That is, it moves in the axial direction.
第2図は能動側結合盤1と受動側結合盤13とがドツキ
ングした状態を示すものである。モータ12の駆動によ
りロッド9が図中右方向に引張られると、レバー5.6
.7がレバー2゜3.4をかさ状に押し広げることによ
り、受動側結合盤13を能動側結合盤1とレバー2,6
゜4とではさみ込む。これらの結合盤を離脱させるとき
は、モータ12を逆方向に駆動してロッド9を図中左に
移動させ、レバー2.5.4を元の状態にして受動側結
合盤16から離れる。FIG. 2 shows a state in which the active side coupling board 1 and the passive side coupling board 13 are docked. When the rod 9 is pulled to the right in the figure by the drive of the motor 12, the lever 5.6
.. 7 pushes the levers 2°3.4 apart into an umbrella shape to connect the passive side coupling board 13 to the active side coupling board 1 and the levers 2 and 6.
Sandwich it with ゜4. When these coupling plates are to be removed, the motor 12 is driven in the opposite direction to move the rod 9 to the left in the figure, and the lever 2.5.4 is returned to its original state and separated from the passive coupling plate 16.
第3図は本発明の他の実施例の概略図であり。FIG. 3 is a schematic diagram of another embodiment of the invention.
第2図に示した実施例におけるロッド9を、能動側結合
盤1aに対して回転可能なシャフト9aに置き換え、シ
ャツ)9aの図中左側の端部におねじを形成してこのお
ねじにはレバー5a。The rod 9 in the embodiment shown in FIG. 2 is replaced with a shaft 9a that is rotatable with respect to the active coupling plate 1a, and a thread is formed at the left end of the shirt 9a in the figure. is lever 5a.
6a、7aの一端とビン結合されたレバー結合部8aが
ねじ結合されている。レバー5a〜7aの他端とそれぞ
れビン結合されたレバー2a〜4aはまた。能動側結合
盤1aとビン結合されている。シャツ)9aの図中右側
の端部には歯車10aが取り付けられ、モータ12aの
回転軸に取り付けられた歯車11aと歯合する。モータ
12aの駆動によりシャフト9aが回転してレバー結合
部8aが図中布に移動すると、レバー結合部8aはレバ
ー2ayBa+4aを押し広げ、受動側結合盤13aを
能動側結合盤1aとレバー2a、3a、4aとではさみ
込む。これらの結合盤を離脱させるには、モータ12a
を逆方向に駆動してレバー結合部8aを図中左に移動さ
せ、レバー2a、3a、4aを元の状態にし、受動側結
合盤13aから遠ざかる。A lever connecting portion 8a is screwed to one end of each of the levers 6a and 7a. The levers 2a to 4a are also coupled to the other ends of the levers 5a to 7a, respectively. It is bin-coupled with the active side coupling board 1a. A gear 10a is attached to the right end of the shirt 9a in the figure, and meshes with a gear 11a attached to the rotating shaft of a motor 12a. When the shaft 9a is rotated by the drive of the motor 12a and the lever coupling part 8a moves to the cloth in the figure, the lever coupling part 8a pushes the levers 2ayBa+4a apart, and the passive side coupling plate 13a is connected to the active side coupling plate 1a and the levers 2a and 3a. , 4a. To detach these coupling boards, the motor 12a
is driven in the opposite direction to move the lever coupling part 8a to the left in the figure, return the levers 2a, 3a, and 4a to their original states, and move away from the passive side coupling board 13a.
以上の実施例は宇宙空間における人工衛星同士や人工衛
星と宇宙基地とのドツキングのみならず、空中、地上に
おける運動体相互のドツキング装置としても適用可能で
ある。The above-described embodiments can be applied not only to docking between artificial satellites in outer space or between a satellite and a space base, but also to docking between moving bodies in the air and on the ground.
以上説明したように本発明は、運動体同士の機械的結合
及び離脱をモータ駆動によるロッドの出し入れまたはシ
ャフトの回転により簡単な操作で、しかも確実に動作す
るドツキング装置を提供することができる。As described above, the present invention can provide a docking device that mechanically connects and disconnects moving bodies with each other with simple operation and reliable operation by moving a rod in and out or rotating a shaft driven by a motor.
以下余白Margin below
第1図は本発明の一実施例でドツキング前の状態を示す
概略図、第2図は第1図のドツキング装置のドツキング
時の状態を示す概略図、第3図は本発明の他の実施例で
ドツキング時の状態を示す概略図、第4図は従来のドツ
キング装置の一例を示す概略図。
1:能動側結合盤、 2,5.4,5.6.7:レパ9
:ロッド、12:モータ、13:受動側結合盤。
第1図
第3図
第2図
第4図FIG. 1 is a schematic diagram showing an embodiment of the present invention in a state before docking, FIG. 2 is a schematic diagram showing a state of the docking device of FIG. 1 during docking, and FIG. 3 is another embodiment of the present invention. FIG. 4 is a schematic diagram showing an example of a state during docking, and FIG. 4 is a schematic diagram showing an example of a conventional docking device. 1: Active side coupling board, 2, 5.4, 5.6.7: Repa 9
: Rod, 12: Motor, 13: Passive side coupling board. Figure 1 Figure 3 Figure 2 Figure 4
Claims (1)
、ドッキングする側の運動体に能動側結合盤を設け、該
能動側結合盤は、その中心部に盤面に対して垂直な方向
に延び、かつ軸方向運動あるいは回転運動可能な軸と、
該軸の軸方向運動あるいは回転運動によりかさ状に開閉
するレバーとを有し、前記ドッキングする側の運動体に
は更に、前記軸を軸方向運動あるいは回転運動させる機
構を設け、ドッキングされる側の運動体の結合部には前
記軸と閉じた状態の前記レバーとが挿通可能な穴を設け
て成るドッキング装置。1. In a docking device used to connect moving bodies, an active side coupling plate is provided on the side of the moving body to be docked, and the active side coupling plate has an axis extending in the direction perpendicular to the plate surface at the center thereof. an axis capable of directional or rotational movement;
a lever that opens and closes in an umbrella shape by axial movement or rotational movement of the shaft; the movable body on the docking side is further provided with a mechanism for axially or rotationally moving the shaft; A docking device comprising a hole through which the shaft and the lever in a closed state can be inserted, in a connecting portion of the moving body.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP63238947A JPH0288400A (en) | 1988-09-26 | 1988-09-26 | Docking device |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP63238947A JPH0288400A (en) | 1988-09-26 | 1988-09-26 | Docking device |
Publications (1)
Publication Number | Publication Date |
---|---|
JPH0288400A true JPH0288400A (en) | 1990-03-28 |
Family
ID=17037652
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP63238947A Pending JPH0288400A (en) | 1988-09-26 | 1988-09-26 | Docking device |
Country Status (1)
Country | Link |
---|---|
JP (1) | JPH0288400A (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2014091022A1 (en) * | 2012-12-14 | 2014-06-19 | Turbodynamics Gmbh | Joining and guiding device |
JP2014228025A (en) * | 2013-05-20 | 2014-12-08 | 独立行政法人 宇宙航空研究開発機構 | Device fixing apparatus and apparatus having the same |
JP2014226974A (en) * | 2013-05-20 | 2014-12-08 | 川崎重工業株式会社 | Space debris removal device retainer using extension spring, and space debris removal device with the same |
EP3647209A1 (en) * | 2018-11-01 | 2020-05-06 | Airbus Defence and Space GmbH | Capture device and capture method for catching uncooperative satellites in space |
-
1988
- 1988-09-26 JP JP63238947A patent/JPH0288400A/en active Pending
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2014091022A1 (en) * | 2012-12-14 | 2014-06-19 | Turbodynamics Gmbh | Joining and guiding device |
US9671458B2 (en) | 2012-12-14 | 2017-06-06 | Turbodynamics Gmbh | System and guided approach device for guiding a handler or a tester together with a device including a test head for electronic components |
JP2014228025A (en) * | 2013-05-20 | 2014-12-08 | 独立行政法人 宇宙航空研究開発機構 | Device fixing apparatus and apparatus having the same |
JP2014226974A (en) * | 2013-05-20 | 2014-12-08 | 川崎重工業株式会社 | Space debris removal device retainer using extension spring, and space debris removal device with the same |
EP3647209A1 (en) * | 2018-11-01 | 2020-05-06 | Airbus Defence and Space GmbH | Capture device and capture method for catching uncooperative satellites in space |
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