JPH0455200A - Apparatus fixing device in spaceshuttle - Google Patents
Apparatus fixing device in spaceshuttleInfo
- Publication number
- JPH0455200A JPH0455200A JP16313890A JP16313890A JPH0455200A JP H0455200 A JPH0455200 A JP H0455200A JP 16313890 A JP16313890 A JP 16313890A JP 16313890 A JP16313890 A JP 16313890A JP H0455200 A JPH0455200 A JP H0455200A
- Authority
- JP
- Japan
- Prior art keywords
- spacecraft
- fitting
- equipment
- attached
- receiving
- 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
- 239000002184 metal Substances 0.000 description 30
- 230000000694 effects Effects 0.000 description 3
- 239000000969 carrier Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
Landscapes
- Manipulator (AREA)
Abstract
Description
【発明の詳細な説明】
［産業上の利用分野］
本発明は、宇宙機に実験装置等の機器を固定するための
、宇宙機における機器固定装置に関するものである。DETAILED DESCRIPTION OF THE INVENTION [Industrial Field of Application] The present invention relates to an equipment fixing device in a spacecraft for fixing equipment such as experimental equipment to the spacecraft.
［従来の技術］
衛星軌道上を循環している人工衛星に対し、地上から実
験装置等の機器を補給したり、人工衛星で使用済み或い
は故障した機器を地」二に回収したりすることが考えら
れている。このような場合、搬送台の役割を果たす宇宙
機（スペスシャトル）に実験装置等の機器を固定し、宇
宙機を地上から打上げて人工衛星に到達させたり、人工
衛星から地上に回収したりする。[Prior art] It is possible to supply equipment such as experimental equipment from the ground to an artificial satellite circulating in a satellite orbit, and to recover used or malfunctioning equipment from the artificial satellite to the ground. It is considered. In such cases, equipment such as experimental equipment is fixed to a spacecraft (SPES Shuttle) that serves as a transport platform, and the spacecraft is launched from the ground to reach the satellite, or retrieved from the satellite to the ground. .
［発明か解決しようとする課題］
このような搬送台の役割を果たす宇宙機に実験装置等の
機器を、地」二と人工衛星との間の飛翔中に脱落しない
ように確実に固定することかでき、また人工衛星におい
ては、搬送台の役割を果たす宇宙機に対して、実験装置
等の機器を簡単に着脱できる機器固定装置の開発が従来
から望まれていた。[Problem to be solved by the invention] To securely secure equipment such as experimental equipment to a spacecraft that serves as a carrier so that it will not fall off during flight between the Earth and the artificial satellite. In the field of artificial satellites, it has been desired to develop equipment fixing devices that can easily attach and detach equipment such as experimental equipment to spacecraft that serve as carriers.
本発明はこのような要望を満たすため、地上と人工衛星
との間の飛翔中は確実に固定され、人工衛星においては
機器を簡単に着脱できるようにした宇宙機における機器
固定装置を提供することを目的とするものである。In order to meet such demands, the present invention provides a device for fixing equipment in a spacecraft, which is securely fixed during flight between the ground and the artificial satellite, and which allows equipment to be easily attached and detached from the artificial satellite. The purpose is to
［課題を解決するための手段］
上記の課題を解決するため本発明は、宇宙機の表面に取
付けられ上面が平らな受金具と、前記宇宙機の表面側に
固定される機器の下面に取付けられ下面が平らで前記受
金具の上面に載置される腐金具と、前記宇宙機の表面に
設けられ前記受金具と腐金具とを固定並びに解放する固
定用クランプと、を備えたことを特徴とする宇宙機にお
ける機器固定装置および、宇宙機の表面に取付けられ上
面が平らな受金具と、前記宇宙機の表面側に固定される
機器の下面に取付けられ下面が平らな腐金具と、前記宇
宙機の表面側に設けられ前記機器を変位させて前記腐金
具の下面を受金具の上面に当接させる引寄せ用クランプ
と、該引寄せ用クランプと共に作動され前記受金具と腐
金具とを固定並びに解放する固定用クランプと、を備え
たことを特徴とする宇宙機における機器固定装置とした
ものである。[Means for Solving the Problems] In order to solve the above-mentioned problems, the present invention provides a receiving bracket that is attached to the surface of a spacecraft and has a flat top surface, and a receiving bracket that is attached to the lower surface of a device that is fixed to the surface side of the spacecraft. A rotary metal fitting having a flat lower surface and placed on the upper surface of the receiving metal fitting, and a fixing clamp provided on the surface of the spacecraft for fixing and releasing the receiving metal fitting and the rotary metal fitting. an equipment fixing device for a spacecraft, a receiving metal fitting with a flat top surface that is attached to the surface of the spacecraft, a rotary metal fitting with a flat bottom surface that is attached to the bottom surface of a device that is fixed to the surface side of the spacecraft; a pulling clamp provided on the surface side of the spacecraft for displacing the equipment and bringing the lower surface of the rotary metal fitting into contact with the upper surface of the receiving metal fitting; A device fixing device for a spacecraft is characterized by comprising a fixing clamp that fixes and releases the device.
［作 用］
固定クランプによって宇宙機の受金具と機器の腐金具と
は確実に結合される。さらに引寄せ用クランプによって
受金具に腐金具が当接され、固定クランプによる受金具
と腐金具との結合を、確実にする。[Function] The fixed clamp securely connects the spacecraft's receiving fittings and the equipment's rotary fittings. Furthermore, the rotary metal fitting is brought into contact with the receiving metal fitting by the pulling clamp, and the connection between the receiving metal fitting and the rotary metal fitting by the fixing clamp is ensured.
［実 施 例］ 以下、本発明の実施例を図面を参照して説明する。[Example] Embodiments of the present invention will be described below with reference to the drawings.
第１１図は人工衛星１の要部を示す斜視図であって、実
験装置等の機器２の着脱部３が人工衛星１の装着部４を
挾んで、機器２を人工衛星１に取付けることができるよ
うになっている。人工衛星１にはマニピュレータ５が設
けてあって、その親アーム６が機器２をつかみ、機器２
０着脱部３を人工衛星１の装着部４に着脱するようにな
っている。FIG. 11 is a perspective view showing the main parts of the artificial satellite 1, in which the attachment/detachment part 3 of the equipment 2 such as an experimental device holds the attachment part 4 of the artificial satellite 1, and the equipment 2 can be attached to the artificial satellite 1. It is now possible to do so. The artificial satellite 1 is provided with a manipulator 5, whose main arm 6 grasps the device 2 and moves the device 2.
The 0 attachment/detachment part 3 is attached to and detached from the attachment part 4 of the artificial satellite 1.
人工衛星１に取付けて使用した実験装置等の機器２は、
取替を必要とすることがある。機器２を取替える場合に
は、第１２図に示す台状の宇宙機７上に新しい機器２を
固定して地上から人工衛星１に向けて打上げ、宇宙機７
が人工衛星１に到達すると、第１１図に示すマニピュレ
ータ５によって新しい機器２を宇宙機７から外して人工
衛星１に取付け、使用済の機器２を人工衛星１から外し
て宇宙機７に固定し、宇宙機７と共に使用済の機器２を
地上に回収する。Equipment 2 such as experimental equipment installed on the artificial satellite 1 is:
May require replacement. When replacing the equipment 2, the new equipment 2 is fixed on the platform-shaped spacecraft 7 shown in FIG.
When the device reaches the satellite 1, the new device 2 is removed from the spacecraft 7 and attached to the satellite 1 using the manipulator 5 shown in FIG. 11, and the used device 2 is removed from the satellite 1 and fixed to the spacecraft 7. , the used equipment 2 is recovered to the ground together with the spacecraft 7.
この場合（機器２を宇宙機７に取付けた状態では）、機
器２を着脱する着脱部３及び装着部４は、打上げ又は回
収時の振動／衝撃荷重には耐えられないような軽量化設
計となっているため、別途（本発明のような）固定装置
が必要となる。In this case (with the equipment 2 attached to the spacecraft 7), the attachment/detachment part 3 and attachment part 4 for attaching and detaching the equipment 2 are designed to be lightweight so that they cannot withstand vibration/shock loads during launch or recovery. Therefore, a separate fixing device (like the one in the present invention) is required.
第１３図は宇宙機７に使用済の機器２を固定する準備を
している状態の側面図であって、宇宙機７には直立した
ガイドレール用ブラケット８が固定されており、ガイド
レール用ブラケット８の正面には、ねじ杆９の回転によ
って昇降する装着部１０が設けである。FIG. 13 is a side view of the spacecraft 7 in preparation for fixing the used equipment 2 to it, and an upright guide rail bracket 8 is fixed to the spacecraft 7. A mounting portion 10 is provided on the front side of the bracket 8 and is moved up and down by the rotation of a screw rod 9.
機器２はマニピュレータの親アーム６につかまれで人工
衛星から外され、機器２の着脱部３を第１４図に示すよ
うに装着部１０に装着した後、マニピュレータの子アー
ム１１によってねじ杆９を回転し、装着部１０を下降す
る。The device 2 is removed from the satellite by being grabbed by the main arm 6 of the manipulator, and after the attachment/detachment part 3 of the device 2 is attached to the attachment part 10 as shown in FIG. 14, the screw rod 9 is rotated by the child arm 11 of the manipulator. Then, the mounting section 10 is lowered.
宇宙機７の表面には受金具１２か取付けられており、機
器２の下面には腐金具１３が取付けられていて、ねじ杆
９を回転して装着部１０と共に機器２が下降すると、第
１５図に示すように腐金具１８が受金具１２の上に載置
されるようになっている。宇宙機７のガイドレール用ブ
ラケッｌ−８には、ねじ杆９のほかに第１６図に示すよ
うにクランプ用回転杆１４か設けてあって、マニピュレ
タの子アーム１１てクランプ用回転杆１４を回転するこ
とかできるようになっている。クランプ用回転杆１４を
回転すると傘歯車１５を介してねじ杆１６が回転し、次
に説明するように受金具１２と脚金具１３とがクランプ
されて、機器２が宇宙機７に強固に固着されるようにな
っている。A receiving metal fitting 12 is attached to the surface of the spacecraft 7, and a rotary metal fitting 13 is attached to the lower surface of the device 2. When the screw rod 9 is rotated and the device 2 is lowered together with the mounting part 10, the 15th As shown in the figure, a rotary metal fitting 18 is placed on the receiving metal fitting 12. In addition to the threaded rod 9, the bracket l-8 for the guide rail of the spacecraft 7 is provided with a rotary rod 14 for clamping as shown in FIG. It is now possible to rotate. When the rotating clamping rod 14 is rotated, the screw rod 16 is rotated via the bevel gear 15, and as will be explained next, the receiving fitting 12 and the leg fitting 13 are clamped, and the equipment 2 is firmly fixed to the spacecraft 7. It is now possible to do so.
第１図は請求項１の発明の一実施例の宇宙機７の平面図
、第２図は第１図の部分的な拡大図、第３図は第１６図
の■−■拡大図であって、第３図に示すような宇宙機７
の表面側に取付けられている受金具Ｉ２は、倒り字状を
して上面が平らになっており、機器２の下面に取付けら
れている脚金具１３は、Ｌ字状をして下面が平らになっ
ていて、第１５図、第１６図で説明したように脚金具１
３が受金具１２の上に載置される場合は、受金具１２上
面の平らな面上に脚金具１３下面の平らな面が当接し、
機器２は宇宙機７の表面上に安定して置かれた状態にな
る。FIG. 1 is a plan view of a spacecraft 7 according to an embodiment of the invention of claim 1, FIG. 2 is a partially enlarged view of FIG. 1, and FIG. 3 is an enlarged view of FIG. Spacecraft 7 as shown in Figure 3
The receiving bracket I2 attached to the front side of the device 2 has an upside down shape with a flat top surface, and the leg bracket 13 attached to the bottom surface of the device 2 has an L shape with a flat bottom surface. The leg metal fittings 1 are flat, as explained in Figs. 15 and 16.
3 is placed on the receiving metal fitting 12, the flat surface of the lower surface of the leg fitting 13 comes into contact with the flat surface of the upper surface of the receiving metal fitting 12,
The equipment 2 is placed stably on the surface of the spacecraft 7.
第１図の宇宙機７上のガイドレール用ブラケット８に設
けであるクランプ用回転杆１４から傘歯車１５を介して
回転されるねじ杆１６には、移動ブロック１７が螺合さ
れている。そして移動ブロック１７には連結杆１８を介
して他の移動ブロック１９が連結されている。移動ブロ
ック１７．１９の側面には第２図に示すようにリンク２
ｏの一端が枢着されていて、リンク２０の他端には、第
３図に示すコ字状の固定用クランプ２１が枢着されてい
る。固定用クランプ２１のコ字状の開口部は受金具１２
および脚金具１３に対向しており、リンク２゜の他端お
よび固定用クランプ２１は、宇宙機７の表面に設けであ
る左右方向の案内溝２２に沿って移動することができる
ようになっている。A moving block 17 is screwed into a screw rod 16 that is rotated via a bevel gear 15 from a rotating clamp rod 14 provided on the guide rail bracket 8 on the spacecraft 7 in FIG. The moving block 17 is connected to another moving block 19 via a connecting rod 18. There are links 2 on the sides of the moving blocks 17 and 19 as shown in Figure 2.
One end of the link 20 is pivotally attached, and a U-shaped fixing clamp 21 shown in FIG. 3 is pivotally attached to the other end of the link 20. The U-shaped opening of the fixing clamp 21 is connected to the receiving metal fitting 12.
The other end of the link 2° and the fixing clamp 21 are movable along a left-right guide groove 22 provided on the surface of the spacecraft 7. There is.
第１６図に示すように受金具１２の上面に脚金具１３の
下面を載置し、マニピュレータの子アーム１１によりク
ランプ用回転杆１４を上から見て時計方向に回転すると
、傘歯車１５を介してねじ杆１６が回転し、移動ブロッ
ク１７はねじ杆１６に沿って第１図、第２図の」三方に
移動し、これと共に連結杆１８に引張られて、他の移動
ブロック１９も第１図、第２図の上方に移動する。移動
ブロック１７．１９か第４図に示すように上方に移動す
ると、リンク２０の内方側の一端も移動ブロック１７．
１９と共に移動し、リンク２０の外方側の他端および固
定用クランプ２１は案内溝２２に沿って外方に移動し、
第５図に示すように固定用クランプ２１のコ字状の開口
部は受金具１２および脚金具１３の水平部分を挾み、受
金具１２と脚金具１３とを当接状態で固定する。これに
よって機器２は、第１６図に示すように着脱部３および
複数の脚金具１３を介して宇宙機７の表面」−に固定さ
れ、宇宙機７が地上と人工衛星１ （第１１図参照）と
の間を飛翔中に、機器２が宇宙機７から脱落することは
ない。As shown in FIG. 16, when the lower surface of the leg fitting 13 is placed on the upper surface of the receiving fitting 12 and the rotating rod 14 for clamping is rotated clockwise when viewed from above by the child arm 11 of the manipulator, the rotating rod 14 is rotated clockwise when viewed from above. The screw rod 16 rotates, and the movable block 17 moves along the screw rod 16 in three directions as shown in FIGS. Move upwards in Figure 2. When the moving block 17.19 moves upward as shown in FIG.
19, the other outer end of the link 20 and the fixing clamp 21 move outward along the guide groove 22,
As shown in FIG. 5, the U-shaped opening of the fixing clamp 21 sandwiches the horizontal portions of the receiving metal fitting 12 and the leg fitting 13, and fixes the receiving metal fitting 12 and the leg fitting 13 in a state of contact. As a result, the equipment 2 is fixed to the surface of the spacecraft 7 via the attachment/detachment part 3 and the plurality of leg fittings 13, as shown in FIG. ) The equipment 2 will not fall off from the spacecraft 7 while flying between them.
宇宙機７が人工衛星ｌまたは地上に到達した後、機器２
を宇宙機７から外す場合には、第１３図から第１６図ま
での操作を逆の順序で行えばよい。After the spacecraft 7 reaches the satellite or the ground, the equipment 2
When removing it from the spacecraft 7, the operations from FIG. 13 to FIG. 16 may be performed in the reverse order.
第６図は請求項２の発明の一実施例の宇宙機７の平面図
、第７図は第６図の部分的な拡大図、第８図は第７図の
■−■拡大図であって、第１図ないし第３図と同一部分
には同一符号を付しである。6 is a plan view of the spacecraft 7 according to an embodiment of the invention of claim 2, FIG. 7 is a partially enlarged view of FIG. 6, and FIG. 8 is an enlarged view of FIG. The same parts as in FIGS. 1 to 3 are designated by the same reference numerals.
第６図に示すように、宇宙機７のガイドレール用ブラケ
ット８に設けである装着部１０に着脱部３を装着した機
器２が宇宙機７の表面に下降すると、機器２の下面に取
付けである脚金具１３が、宇宙機７の表面に取付けであ
る受金具１２の」二に載置されるようになっていて、脚
金具１３および受金具１２は、第３図に示したものと同
じ構造になっている。宇宙機７には、機器２，２．・・
・の下側中央付近で左右方向に位置するようにねじ杆１
６か設けてあって、図示しないマニピュレタの子アーム
によってクランプ用回転杆１４を回転すると、ねじ杆１
６が回転されるようになっている。As shown in FIG. 6, when the device 2 with the detachable part 3 attached to the attachment part 10 provided on the guide rail bracket 8 of the spacecraft 7 descends to the surface of the spacecraft 7, the device 2 cannot be attached to the bottom surface of the spacecraft 7. A certain leg fitting 13 is placed on the second part of the receiving fitting 12 attached to the surface of the spacecraft 7, and the leg fitting 13 and the receiving fitting 12 are the same as those shown in FIG. It has a structure. The spacecraft 7 has devices 2, 2 .・・・
・Insert the screw rod 1 so that it is located horizontally near the center of the bottom.
6 is provided, and when the clamp rotary rod 14 is rotated by a child arm of a manipulator (not shown), the screw rod 1
6 is rotated.
ねじ杆１６には、宇宙機７の表面に固定される機器２，
２．・・・の個数と同じ個数の移動ブロック２３か螺合
されていて、各ブロック２３の前後両端には、第７図に
示すように、それぞれリンク２４の一端か枢着されてい
る。リンク２４の他端には２本のリンク２０．２０の一
端か枢着されていて、これらの互に枢着されているリン
ク２４の他端とリンク２０．２０の一端とは、宇宙機７
（第６図参照）の表面に前後方向に設けである案内溝
２５に沿って移動できるようにされている。リンク２ｏ
の他端には、第３図、第５図に示した固定用クランプ２
１と同じ構造をしたコ字状の固定用クランプ２１が枢着
されていて、固定用クランプ２１のコ字状の開口部は受
金具１２および腐金具１３に対向しており、リンク２０
の他端および固定用クランプ２１は、宇宙機７の表面に
設けである左右方向の案内溝２２に沿って移動できるよ
うになっている。The screw rod 16 has equipment 2 fixed to the surface of the spacecraft 7,
2. The same number of movable blocks 23 are screwed together, and one end of a link 24 is pivotally connected to the front and rear ends of each block 23, as shown in FIG. 7. One end of two links 20.20 is pivotally connected to the other end of the link 24, and the other end of the link 24 and one end of the link 20.20, which are pivotally connected to each other, are connected to the spacecraft 7.
(See FIG. 6) so that it can move along a guide groove 25 provided in the front and back direction on the surface of the body. link 2o
At the other end, there is a fixing clamp 2 shown in FIGS. 3 and 5.
A U-shaped fixing clamp 21 having the same structure as 1 is pivotally mounted, and the U-shaped opening of the fixing clamp 21 faces the receiving fitting 12 and the rotary fitting 13, and the link 20
The other end and the fixing clamp 21 are movable along a left-right guide groove 22 provided on the surface of the spacecraft 7.
移動ブロック２３の左右両側の若干離れた位置には、ね
じ杆１６に螺合した引寄せ用クランプ２６が設けられて
いる。引寄せ用クランプ２６は第８図に示すように、宇
宙機７の表面の上方で水平方向に屈折したアーム２７と
、宇宙機７の表面裏側真下で水平方向に延びているアー
ム２８とを備えていて、アーム２７．２８の先端にはロ
ーラー２９゜３０が取付けられ、ローラー３０は宇宙機
７の表面裏側に接するようになっている。Pulling clamps 26 screwed onto the threaded rods 16 are provided at slightly distant positions on both the left and right sides of the moving block 23. As shown in FIG. 8, the pulling clamp 26 includes an arm 27 bent horizontally above the surface of the spacecraft 7 and an arm 28 extending horizontally just below the back side of the surface of the spacecraft 7. Rollers 29 and 30 are attached to the tips of the arms 27 and 28, and the rollers 30 are in contact with the back side of the surface of the spacecraft 7.
一方、機器２の下面には引寄せ用突起３１が設けてあっ
て、引寄せ用突起３１の引寄せ用クランプ２６側の上面
には、傾斜面３２が形成されている。On the other hand, a pulling protrusion 31 is provided on the lower surface of the device 2, and an inclined surface 32 is formed on the upper surface of the pulling protrusion 31 on the pulling clamp 26 side.
また宇宙機７の表面上にはスプリング３３が取付けてあ
って、機器２の着脱部３ （第６図参照）を装着部ｌＯ
に装着して下降すると、第８図に示すように引寄せ用突
起３１がスプリング３３の上端に当接するようになって
いる。Further, a spring 33 is attached to the surface of the spacecraft 7, and a spring 33 is attached to the surface of the spacecraft 7 to connect the attachment/detachment part 3 (see Fig. 6) of the equipment 2 to the attachment part lO.
When the spring 33 is lowered, the drawing protrusion 31 comes into contact with the upper end of the spring 33, as shown in FIG.
機器２の着脱部３を装着部１０に装着して下降し、引寄
せ用突起３１がスプリング３３の上端に当接した状態で
第７図のクランプ用回転杆１４を回転し、傘歯車】５を
介してねじ杆１６を第７図の右方から見て時計方向に回
転させると、移動ブロック２３および引寄せ用クランプ
２６は、ねじ杆１６に沿って第７図の右方に移動し、第
９図、第１０図に示す状態になる。The detachable part 3 of the device 2 is attached to the attachment part 10 and lowered, and with the pulling protrusion 31 in contact with the upper end of the spring 33, the rotating clamping rod 14 shown in FIG. 7 is rotated, and the bevel gear]5 When the screw rod 16 is rotated clockwise when viewed from the right side in FIG. 7 through The state will be as shown in FIGS. 9 and 10.
引寄せ用クランプ２６が第１０図に示すように右方に移
動すると、アーム２７先端のローラー２９が引寄せ用突
起３１の傾斜面３２を下方に押し、引寄せ用突起３１を
介して機器２を下方に引寄せる。When the pulling clamp 26 moves to the right as shown in FIG. pull downward.
これによって機器２の下面に取付けられている腐金具１
３の下面は、受金具１２の上面に確実に当接し、浮き上
った状態になることがない。As a result, the rotary metal fitting 1 attached to the bottom surface of the device 2
The lower surface of 3 reliably abuts the upper surface of the receiving metal fitting 12, and does not rise up.
一方、移動ブロック２３が第７図の状態から右方に移動
して第９図の状態になると、リンク２４の他端およびリ
ンク２０の一端は案内溝２５に沿って移動ブロック２３
から離れる方向に移動し、リンク２０の外方側の他端お
よび固定用クランプ２１は案内溝２２に沿って外方に移
動して、受金具１２と腐金具１３とを当接状態で固定す
る。On the other hand, when the moving block 23 moves rightward from the state shown in FIG. 7 to the state shown in FIG. 9, the other end of the link 24 and one end of the link 20 move along the guide groove 25 and
The other outer end of the link 20 and the fixing clamp 21 move outward along the guide groove 22 to fix the receiving fitting 12 and the rotary fitting 13 in contact with each other. .
このように第６図ないし第１０図に示す請求項２の発明
においては、引寄せ用クランプ２６によって腐金具１３
を受金具１２に確実に当接させると同時に受金具１２と
腐金具１３とが固定され、機器２は宇宙機７の表面上に
確実に固定される。機器２を宇宙機７から外す場合には
、第６図のクランプ用回転杆１４、傘歯車１５を介して
ねじ杆１６を第９図の右方から見て反時計方向に回転す
れば、引寄せ用クランプ２６のローラー２９は引寄せ用
突起３１の傾斜面３２から離れ、同時に固定用りランプ
２１は受金具１２および腐金具１３から外れる。In this manner, in the invention of claim 2 shown in FIGS. 6 to 10, the fastener 13 is
At the same time, the receiving fitting 12 and the rotary fitting 13 are fixed, and the equipment 2 is securely fixed on the surface of the spacecraft 7. When removing the device 2 from the spacecraft 7, the screw rod 16 is rotated counterclockwise when viewed from the right side of FIG. 9 via the clamp rotary rod 14 and the bevel gear 15 shown in FIG. The roller 29 of the pulling clamp 26 separates from the inclined surface 32 of the pulling projection 31, and at the same time, the fixing lamp 21 comes off from the receiving fitting 12 and the rotary fitting 13.
［発明の効果］
本発明は、機器下面の腐金具と宇宙機表面の受金具が固
定用クランプによって固定されるので、機器が宇宙機に
確実に固定されて飛翔中に脱落することがなく、また取
外す際にはコンピュータ又はモータ（図示路）等を用い
て自動的に簡単に取外すことができる。[Effects of the Invention] In the present invention, since the rotary metal fittings on the bottom surface of the equipment and the receiving metal fittings on the surface of the spacecraft are fixed by the fixing clamp, the equipment is securely fixed to the spacecraft and does not fall off during flight. In addition, when removing it, it can be automatically and easily removed using a computer or a motor (as shown in the diagram).
さらに、請求項２の発明は、上記の効果のほかに、腐金
具が固定金具に対して確実に引寄せられて当接され、固
定を確実にする効果がある。Furthermore, the invention of claim 2 has an effect that, in addition to the above-mentioned effects, the rotary metal fittings are reliably drawn to and abutted against the fixing metal fittings, thereby ensuring secure fixation.
第１図は請求項１の発明の一実施例の宇宙機の平面図、
第２図は第１図の部分的な拡大図、第３図は第１６図の
■−■拡大図、第４図、第５図はそれぞれ第２図、第３
図とは異なる状態を示す拡大図、第６図は請求項２の発
明の一実施例の宇宙機の平面図、第７図は第６図の部分
的な拡大図、第８図は第７図の■−■拡大図、第９図、
第１０図はそれぞれ第７図、第８図とは異なる状態を示
す拡大図、第１１図は人工衛星の要部を示す斜視図、第
１２図は宇宙機の斜視図、第１３図ないし第１６図は機
器を宇宙機に取付ける順序を示す側面図である。
図中、２は機器、７は宇宙機、１２は受金具、１３は腐
金具、２１は固定用クランプ、２６は引寄せ用クランプ
を示す。FIG. 1 is a plan view of a spacecraft according to an embodiment of the invention of claim 1;
Figure 2 is a partially enlarged view of Figure 1, Figure 3 is an enlarged view of Figure 16, and Figures 4 and 5 are Figures 2 and 3, respectively.
6 is a plan view of a spacecraft according to an embodiment of the invention of claim 2, FIG. 7 is a partially enlarged view of FIG. 6, and FIG. ■-■Enlarged view of figure, Figure 9,
Fig. 10 is an enlarged view showing a state different from Fig. 7 and Fig. 8, respectively, Fig. 11 is a perspective view showing the main parts of the artificial satellite, Fig. 12 is a perspective view of the spacecraft, and Figs. FIG. 16 is a side view showing the order in which equipment is attached to the spacecraft. In the figure, 2 is a device, 7 is a spacecraft, 12 is a receiving metal fitting, 13 is a rotary metal fitting, 21 is a fixing clamp, and 26 is a pulling clamp.
Claims (1)
前記宇宙機の表面側に固定される機器の下面に取付けら
れ下面が平らで前記受金具の上面に載置される脚金具と
、前記宇宙機の表面に設けられ前記受金具と脚金具とを
固定並びに解放する固定用クランプと、を備えたことを
特徴とする宇宙機における機器固定装置。 ２）宇宙機の表面に取付けられ上面が平らな受金具と、
前記宇宙機の表面側に固定される機器の下面に取付けら
れ下面が平らな脚金具と、前記宇宙機の表面側に設けら
れ前記機器を変位させて前記脚金具の下面を受金具の上
面に当接させる引寄せ用クランプと、該引寄せ用クラン
プと共に作動され前記受金具と脚金具とを固定並びに解
放する固定用クランプと、を備えたことを特徴とする宇
宙機における機器固定装置。[Claims] 1) A receiving bracket that is attached to the surface of a spacecraft and has a flat top surface;
A leg fitting that is attached to the lower surface of a device fixed to the surface side of the spacecraft and has a flat lower surface and is placed on the upper surface of the receiving fitting; and a leg fitting that is provided on the surface of the spacecraft and the receiving fitting and the leg fitting. An equipment fixing device for a spacecraft, characterized by comprising a fixing clamp that fixes and releases the equipment. 2) A bracket that is attached to the surface of the spacecraft and has a flat top surface;
A leg fitting with a flat bottom surface attached to the lower surface of a device fixed to the front side of the spacecraft, and a leg fitting provided on the front side of the spacecraft by displacing the device so that the lower surface of the leg fitting is attached to the top surface of the receiving bracket. A device fixing device for a spacecraft, comprising: a pulling clamp that is brought into contact with the pulling clamp; and a fixing clamp that is operated together with the pulling clamp to fix and release the receiving fitting and the leg fitting.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP16313890A JPH0455200A (en) | 1990-06-21 | 1990-06-21 | Apparatus fixing device in spaceshuttle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP16313890A JPH0455200A (en) | 1990-06-21 | 1990-06-21 | Apparatus fixing device in spaceshuttle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH0455200A true JPH0455200A (en) | 1992-02-21 |
Family
ID=15767931
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP16313890A Pending JPH0455200A (en) | 1990-06-21 | 1990-06-21 | Apparatus fixing device in spaceshuttle |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH0455200A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS61291527A (en) * | 1985-06-19 | 1986-12-22 | Teijin Ltd | Selective adsorbent and separation and recovery of human alpha-plasmin inhibitor |
| JP2008135328A (en) * | 2006-11-29 | 2008-06-12 | Ishizaki Honten:Kk | Connection structure of electric components, and vehicular lighting fixture |
| US7387276B1 (en) * | 2004-11-24 | 2008-06-17 | West Virginia University | Aerial sensor pod deployment system |
-
1990
- 1990-06-21 JP JP16313890A patent/JPH0455200A/en active Pending
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS61291527A (en) * | 1985-06-19 | 1986-12-22 | Teijin Ltd | Selective adsorbent and separation and recovery of human alpha-plasmin inhibitor |
| JPH0643440B2 (en) * | 1985-06-19 | 1994-06-08 | 帝人株式会社 | Method for separating and recovering human α2-plasmin inhibitor |
| US7387276B1 (en) * | 2004-11-24 | 2008-06-17 | West Virginia University | Aerial sensor pod deployment system |
| JP2008135328A (en) * | 2006-11-29 | 2008-06-12 | Ishizaki Honten:Kk | Connection structure of electric components, and vehicular lighting fixture |
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