JPS62103300A - Fixture for space apparatus - Google Patents
Fixture for space apparatusInfo
- Publication number
- JPS62103300A JPS62103300A JP60242880A JP24288085A JPS62103300A JP S62103300 A JPS62103300 A JP S62103300A JP 60242880 A JP60242880 A JP 60242880A JP 24288085 A JP24288085 A JP 24288085A JP S62103300 A JPS62103300 A JP S62103300A
- Authority
- JP
- Japan
- Prior art keywords
- space
- equipment
- facility structure
- gripping
- stopper
- 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
- Devices For Use In Laboratory Experiments (AREA)
- Magnetic Resonance Imaging Apparatus (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】
〔産業上の利用分野〕
本発明は、宇宙現象の観測等を行なう宇宙用機器を軌道
上に構築された宇宙施設構造体へ取付けるための取付装
置に関するものである。DETAILED DESCRIPTION OF THE INVENTION [Industrial Application Field] The present invention relates to a mounting device for mounting space equipment for observing space phenomena, etc. to a space facility structure built on orbit.
例えば三菱重工名古屋航空機製作所発行のパンツレフト
「宇宙開発Ｊ Ｎｏ、０４５ （ＩＢ）Ｈの第１５頁に
紹介されているように地球軌道上等の宇宙空間に長期間
滞留し、各種の実験、サービス提供等を行なうための宇
宙用施設の建設が近時計画されている。このような宇宙
用施設においては、宇宙塵の観測、太陽観測などの各種
宇宙現象観測を行なうために必要な機材、およびその他
の実験、通信に必要な機材（宇宙用機器）を宇宙機外に
建設した宇宙施設構造体上に配置することがある。とこ
ろで、宇宙用施設の建設やその後の活動のためには、必
要機材、人員の打ち上げ、地上施設からのバックアップ
など莫大な費用を要する。For example, as introduced on page 15 of "Space Development J No. 045 (IB)H" published by Mitsubishi Heavy Industries, Nagoya Aircraft Manufacturing Co., Ltd., a spacecraft that stays in outer space for a long period of time, such as in Earth orbit, conducts various experiments and services. Recently, there are plans to construct space facilities for the purpose of providing space services, etc.Such space facilities will be equipped with the equipment necessary to observe various space phenomena such as space dust observations and solar observations, as well as other equipment. Equipment (space equipment) necessary for experiments and communications may be placed on a space facility structure built outside the spacecraft.By the way, for the construction of space facilities and subsequent activities, the necessary equipment , launching personnel, backing up from ground facilities, etc. requires enormous costs.
また、宇宙用施設には数多くの指命が課せられている。Additionally, space facilities are subject to numerous instructions.
このため宇宙用施設での活動は可能な限り効率よく遂行
されなければならない。Therefore, activities at space facilities must be carried out as efficiently as possible.
従来、宇宙用機器を軌道上で建設された宇宙施設構造体
に取付ける手段としては、ネジ結合あるいは機械的ラッ
チによる結合が考えられた。すなわち、ネジ結合の場合
、宇宙用マニピュレータの操作によって取付けるべき宇
宙用機器を予め設定された取付個所へ運び、かつマニピ
ュレータ操作によって宇宙施設構造体へのネジ固定作業
を行なう、また、機械的ラッチによる結合の場合には、
宇宙用マニピュレータの操作によって宇宙用機器を予め
定められた所定個所へ運び、当該所定位置でラッチ装置
を作動させ、宇宙用機器を固定するものである。Conventionally, screw connections or mechanical latches have been considered as means for attaching space equipment to space facility structures constructed in orbit. In other words, in the case of screw connection, the space equipment to be attached is transported to a preset installation location by operating a space manipulator, and the screw is fixed to the space facility structure by operating the manipulator. In case of a join,
Space equipment is transported to a predetermined location by operating a space manipulator, and a latch device is activated at the predetermined location to secure the space equipment.
ところで、このような従来の結合構造にあっては、宇宙
構造体側に設けた結合用のネジ孔あるいはラッチ装置の
位置へ宇宙用機器を運ぶ場合に、結合個所の重合など正
確な位置調整を行なう必要がある。しかしながら、宇宙
機からのマニピュレータ操作によって正確な位置調整を
行なうには、マニピュレータ操作が煩雑となり、作業性
が悪いという問題がある。By the way, in such a conventional coupling structure, when transporting space equipment to the location of the coupling screw hole or latch device provided on the space structure side, it is necessary to perform accurate positional adjustment such as overlapping the coupling points. There is a need. However, in order to perform accurate position adjustment by manipulator operation from the spacecraft, there is a problem that the manipulator operation is complicated and workability is poor.
そこで本発明の課題は宇宙用機器の取付けの際における
位置調整を容易にする点にある。Therefore, an object of the present invention is to facilitate position adjustment when installing space equipment.
前記課題を達成して従来技術の問題点を解決するため、
本発明に係る宇宙用機器の取付装置は、宇宙用機器、宇
宙施設構造体のどちらか一方に配設される係合手段と他
方に配設される把持手段とからなり、前記係合手段には
電磁石となることのできる凸部を設けるとともに、前記
把持手段には電磁石となることができ、かつ前記凸部を
抱持することのできる四部を設け、かつ係合手段と把持
手段の少なくとも一方に非電磁石状態における両者の結
合状態を維持できるストッパを設けた。In order to achieve the above-mentioned problems and solve the problems of the conventional technology,
A mounting device for space equipment according to the present invention includes an engaging means disposed on either one of the space equipment or a space facility structure, and a gripping means disposed on the other, and the above-mentioned engaging means is provided with a protrusion that can serve as an electromagnet, and the gripping means is provided with four parts that can serve as an electromagnet and can hold the protrusion, and at least one of the engaging means and the gripping means A stopper was provided to maintain the bonded state between the two in the non-electromagnetic state.
本発明にあっては、係合手段、把持手段のいずれか一方
を宇宙用機器、宇宙施設構造体に配設する。宇宙用機器
を宇宙施設構造体に取付けるには、マニピュレータ操作
等により宇宙用機器を取付個所近傍へ運搬する。そして
、通電によって係合手段の凸部と把手手段の凹部を互い
に異なる磁極の電磁石とし、磁力制御による位置調整を
行なった後、凸部と凹部とを結合させる。このとき、係
合手段、把持手段のうち少なくとも一方に設けられたス
トッパが作動し、両者は電源供給が停止されて非電磁石
状態となった後も結合状態を維持する。他方、宇宙用機
器を取外すときには、前記凸部と凹部とを同極の電極石
とする。宇宙空間（軌道周回中の宇宙用施設系）は無重
力であるから１両電磁石の反発力によりストッパによる
結合状態が解除され、宇宙用機器は宇宙施設構造体から
離れる。In the present invention, either the engaging means or the gripping means is provided in the space equipment or the space facility structure. To attach space equipment to a space facility structure, the space equipment is transported to the vicinity of the installation location using a manipulator or the like. Then, by applying electricity, the convex portion of the engaging means and the concave portion of the handle means are made into electromagnets with different magnetic poles, and after position adjustment is performed by magnetic force control, the convex portion and the concave portion are combined. At this time, a stopper provided on at least one of the engaging means and the gripping means is activated, and the coupled state between the two is maintained even after the power supply is stopped and the two are in a non-electromagnetic state. On the other hand, when the space equipment is removed, the convex portion and the concave portion are used as electrode stones of the same polarity. Since outer space (orbiting space facility system) is weightless, the repulsive force of both electromagnets releases the coupling state by the stopper, and the space equipment separates from the space facility structure.
以下、添付図面に基づいて本発明の詳細な説明する。 Hereinafter, the present invention will be described in detail based on the accompanying drawings.
第１図および第２図には、本発明に係る宇宙用機器の取
付装置の一例を示すものである。この取付装置１は、宇
宙用機器２側に固定した保合装置３と宇宙施設構造体に
取付けた把持装置４とからなる。この実施例では凹形状
をなす把持装置４を宇宙施設構造体側に固定するものと
して説明する。FIGS. 1 and 2 show an example of a mounting device for space equipment according to the present invention. This attachment device 1 consists of a holding device 3 fixed to the space equipment 2 side and a gripping device 4 attached to the space facility structure. In this embodiment, the gripping device 4 having a concave shape will be explained as being fixed to the space facility structure side.
第３図および第４図は把持装置４を固定する宇宙施設構
造体５を示すものである。図において７は宇宙施設構造
体５と宇宙機（図示せず）とを接続するインターフェー
ス、８は宇宙施設構造体５を覆う耐熱パネル、９は宇宙
施設構造体５を構成するトラス部材である。耐熱パネル
８は第５図および第６図に示すように、透明パネル内に
電熱線１１を配設するとともにパネル内に冷媒用流路１
２を有し、配設固定された宇宙用機器２を宇宙空間にお
ける熱環境から保護する。第５図中、符号１３は宇宙機
から前記インターフェース７およびトラス部材９を介し
て電熱線１１に電源を供給するコネクタ、１４は宇宙機
からトラス部材９を介して冷媒（例えばＬＮ２）を供給
する冷媒用フィッティングである。尚、トラス部材９は
第７図に示すように外壁１５と内壁１６とから成り、外
壁１５と内壁１６との間には断熱材１７を設け、該断熱
材１７内にワイヤーハーネス１８を設ける一方、内壁１
６には冷媒用流路１９が形成されている。そして、トラ
ス部材９の接合部には冷媒の流路を切換える切換弁（図
示せず）を設け、温度制御を行なうべき耐熱パネル８に
冷媒を送るようになっている、尚、１３’は耐熱パネル
８に対応して設けられたトラス部材９側のコネクタ、１
４′はトラス部材９側の冷媒用フィッティングである。3 and 4 show the space facility structure 5 to which the gripping device 4 is fixed. In the figure, 7 is an interface that connects the space facility structure 5 and a spacecraft (not shown), 8 is a heat-resistant panel that covers the space facility structure 5, and 9 is a truss member that constitutes the space facility structure 5. As shown in FIGS. 5 and 6, the heat-resistant panel 8 has a heating wire 11 disposed inside the transparent panel and a refrigerant channel 1 inside the panel.
2, and protects the fixed space equipment 2 from the thermal environment in outer space. In FIG. 5, reference numeral 13 is a connector for supplying power from the spacecraft to the heating wire 11 via the interface 7 and truss member 9, and 14 is a connector for supplying a coolant (for example, LN2) from the spacecraft via the truss member 9. This is a refrigerant fitting. The truss member 9 is made up of an outer wall 15 and an inner wall 16 as shown in FIG. , inner wall 1
A refrigerant flow path 19 is formed in 6 . A switching valve (not shown) for switching the flow path of the refrigerant is provided at the joint of the truss member 9, and the refrigerant is sent to the heat-resistant panel 8 where temperature control is to be performed. A connector on the truss member 9 side provided corresponding to the panel 8, 1
4' is a refrigerant fitting on the truss member 9 side.
第８図は、かかるトラス部材９に把持装置４を固定した
状態を示すものである０把持装置４は、トラス部材９同
士が交差する個所に配設されるものであり、固定部材２
１によってその基部が固定される。尚、図中２２は固定
部材２１の動きを制限するためのストッパである。宇宙
用機器２は、このようにしてトラス部材９に固定された
把持装置４および該把持装置４に結合した係合装置３を
介して宇宙施設構造体５に取付けられる。FIG. 8 shows a state in which the gripping device 4 is fixed to the truss member 9. The gripping device 4 is disposed at a location where the truss members 9 intersect with each other, and
1 fixes its base. In addition, 22 in the figure is a stopper for restricting the movement of the fixing member 21. The space equipment 2 is thus attached to the space facility structure 5 via the gripping device 4 fixed to the truss member 9 and the engagement device 3 coupled to the gripping device 4.
第１図に戻り、この取付装置ｌの構成を説明する。Returning to FIG. 1, the configuration of this mounting device 1 will be explained.
宇宙用機器２に固定される係合装置３は、取付面２３か
ら立上がるガイドコーン２４を有する。The engagement device 3 fixed to the space equipment 2 has a guide cone 24 rising from a mounting surface 23.
ガイドコーン２４は、電磁石となって磁界を形成するこ
とができるものであり、円錐形状をなした円錐部２５と
、円錐部２５から更に先端に延びる円柱部２６からなる
０円柱部２６にはその軸方向に垂直にスプリング２７を
配設するとともに該スプリング２７の両端に鋼球２８を
設けることにより、係合装置３と把持装置４の結合状態
を維持させるストッパ３０を形成する。また、円柱部２
６の先端にはガイドコーン２４と逆向きの円錐形状をな
し、その基底部の直径が円柱部２６の先端面と同一寸法
に形成されたガイドピン３１を設ける。The guide cone 24 functions as an electromagnet and can form a magnetic field, and has a cylindrical portion 26 consisting of a conical portion 25 and a cylindrical portion 26 extending from the conical portion 25 to the tip. By arranging a spring 27 perpendicular to the axial direction and providing steel balls 28 at both ends of the spring 27, a stopper 30 is formed that maintains the coupled state of the engagement device 3 and the gripping device 4. In addition, the cylindrical part 2
A guide pin 31 is provided at the distal end of the guide cone 24 and has a conical shape facing oppositely to the guide cone 24 and whose base has the same diameter as the distal end surface of the cylindrical portion 26 .
他方、宇宙施設構造体５側に固定される把持装置４は、
前記ガイドコーン２４と接合できる円錐面３２を有する
ガイド部３３と、前記ガイドピン３１および円柱部２６
よりも若干大きな径のグループ３４を有するシリンダ部
３５とから構成される。ガイド部３３は、前記ガイドコ
ーン２４と同様に電磁石となって磁界を形成することが
できる。また、シリンダ部３５には、前記ストッパ３０
の鋼球２８が嵌合できる程度の径を有する孔部３６を形
成するとともに、グループ３４内には前記係合装置３の
急直な結合を防止して宇宙用機器２を衝撃から保護する
とともにその押圧力により分離時の結合解除を容易にす
るためのコイルノくネ３７を設ける。尚、３８は前記ガ
イドピン３１にコイルバネ３７のばね力を均一に伝達さ
せるためのキャッププレートである。On the other hand, the gripping device 4 fixed to the space facility structure 5 side is
A guide portion 33 having a conical surface 32 that can be joined to the guide cone 24, the guide pin 31 and the cylindrical portion 26.
The cylinder part 35 has a group 34 having a diameter slightly larger than that of the cylinder part 35. The guide portion 33, like the guide cone 24, can function as an electromagnet and form a magnetic field. Further, the cylinder portion 35 is provided with the stopper 30.
A hole 36 having a diameter large enough to fit the steel ball 28 is formed in the group 34, and a hole 36 is formed in the group 34 to prevent the engagement device 3 from being joined suddenly and protect the space equipment 2 from impact. A coil cutout 37 is provided to facilitate the release of the connection during separation using the pressing force. Note that 38 is a cap plate for uniformly transmitting the spring force of the coil spring 37 to the guide pin 31.
次に作用を説明する。Next, the effect will be explained.
宇宙用機器２の取付けの場合は、まず当該宇宙用機器２
をマニピュレータによって把持装置４の近傍個所へ運搬
する。次に、ガイドコーン２４およびガイド部３３に組
込まれたコイル（図示せず）に通電し、互いに異なる極
の磁界を形成する。このとき、位置調整に多少の誤差が
あっても、磁極の通−主制御によってその誤差を許容範
囲内まで少なくすることができる。そして、このような
位置調整の後、磁力による吸引あるいはマニピュレータ
による抑圧によって係合装置３を把持装置４に結合させ
る。第２図に示すように、ガイドピン３１がコイルバネ
３７に抗してグループ３４内の所定位置まで達すると、
スプリング２７の伸展により鋼球２８が孔部３６に嵌合
する。これによって係合装置３と把持装置４との結合が
終了する。ここで通電を停止し、ガイドコーン２４とガ
イド部３３を電磁石状態から解除する。係合装置３はス
トッパ３０によって上方への動きが制限されているから
、通電を停止しても把持装置４から分離しない、尚、コ
イルバネ３７のばね力はストッパ３０の解除をしないよ
う予め調整しておくことは勿論である。When installing space equipment 2, first install the space equipment 2.
is transported to a location near the gripping device 4 by a manipulator. Next, the coils (not shown) incorporated in the guide cone 24 and the guide portion 33 are energized to form magnetic fields with different polarities. At this time, even if there is some error in the position adjustment, the error can be reduced to within an allowable range by the main control of the magnetic poles. After such position adjustment, the engaging device 3 is coupled to the gripping device 4 by magnetic attraction or suppression by a manipulator. As shown in FIG. 2, when the guide pin 31 reaches a predetermined position within the group 34 against the coil spring 37,
As the spring 27 expands, the steel ball 28 fits into the hole 36. This completes the coupling between the engaging device 3 and the gripping device 4. At this point, the energization is stopped, and the guide cone 24 and guide portion 33 are released from the electromagnetic state. Since the upward movement of the engagement device 3 is restricted by the stopper 30, it will not separate from the gripping device 4 even if the energization is stopped. Note that the spring force of the coil spring 37 must be adjusted in advance so as not to release the stopper 30. Of course, you should keep it.
一方、宇宙用機器２を取外す場合は、通電によりガイド
コーン２４とガイド部３３を同極の電極石とし、その反
発力およびコイルバネ３７の付勢力によってストッパ３
０の解除を行なう、軌道周回中の宇宙施設系は無重力状
態にあるから、ストッパ３０の解除後、磁極強度を適当
にバランスさせることにより宇宙用機器２を宇宙施設構
造体５から一定の距離に保つことも可能である。On the other hand, when removing the space equipment 2, the guide cone 24 and the guide part 33 are turned into electrode stones of the same polarity by energization, and the repulsion force and the biasing force of the coil spring 37 are used to stop the stopper 3.
Since the space facility system in orbit is in a zero gravity state, after the stopper 30 is released, the space equipment 2 is kept at a certain distance from the space facility structure 5 by appropriately balancing the magnetic pole strength. It is also possible to keep it.
尚、以上の説明では凸部を有する保合手段を宇宙用機器
側に固定し、凹部を有する把持手段を宇宙用施設構造体
側に固定するものとして説明したが、係合手段を宇宙施
設構造体側に、把持手段を宇宙用機器側に固定しても良
い、また、両手段の分離を防止するためのストッパは把
持手段側に設けることもできる。また、係合手段の凸部
１把持手段の凹部は前記実施例の形状に限定されない。In addition, in the above explanation, the retaining means having a convex portion is fixed to the space equipment side, and the gripping means having a concave portion is fixed to the space facility structure side, but the engaging means is fixed to the space facility structure side. Additionally, the gripping means may be fixed to the space equipment side, and a stopper for preventing separation of both means may be provided on the gripping means side. Further, the shape of the convex portion of the engaging means 1 and the concave portion of the gripping means is not limited to the shape of the above embodiment.
以上説明したように、本発明に係る宇宙用機器の取付装
置は凸部を有する保合手段と四部を有する把持手段とを
電磁石となるように構成したから、供給電流の制御によ
る磁力制御によって宇宙用機器の取付けに際しての位置
調整が容易となり、作業性が向上する。As explained above, in the mounting device for space equipment according to the present invention, the holding means having the convex portion and the gripping means having four portions are configured to act as electromagnets, so that the mounting device for space equipment according to the present invention can be used in space by controlling the magnetic force by controlling the supplied current. This makes it easier to adjust the position when installing equipment, improving work efficiency.
第１図および第２図は本発明に係る宇宙用機器の取付装
置を示す断面図、第３図は宇宙施設構造体を示す側面図
、第４図は第３図の■矢視図、第早
５図は耐熱パネルを示す斜視図、第６図は第５の■−■
線断面図、第７図はトラス部材の内部構造を示す断面図
、第８図は本発明令孫る取付装置の使用状態の一例を示
す斜視図である。
１・・・取付装置 ２・・・宇宙用機器３・・・
係合装置 ４・・・把持手段５・・・宇宙施設構
造体 ８・・・耐熱パネル９・・・トラス部材 ２
４・・・ガイドコーン３０・・・ストッパ ３１・
・・ガイドピン３３・・・ガイド部 ３５・・・シ
リンダ部３７・・・コイルバネ
３８・・・キャッププレート
第 １ ｒＡ
２３ 貝又イ１面
３ｌ−ｊｌ”イドぴン２４−−Ｄ’（）”］−ン
３２ 円ｕＬ面２５ 円ｆ１
舒 ３３− ｆイト靜２６
円才主、告Ｐ
３４−７°ル−フ゛２７ スブリノク゛
３５ シリンタ′訃２８・鋼球
３６ 孔卸３０−ストッパ
３７ コイルハ゛ネ３８・ キヤ・
ソアアレート
第２図
へ
第３ｍ
第４図
第５ｖＡ
８（ｍｌ鴫Ｉｖ粕し）
■
第６図1 and 2 are cross-sectional views showing a mounting device for space equipment according to the present invention, FIG. 3 is a side view showing a space facility structure, and FIG. 4 is a view in the direction of the ■ arrow in FIG. Figure 5 is a perspective view showing the heat-resistant panel, Figure 6 is the 5th ■-■
FIG. 7 is a cross-sectional view showing the internal structure of the truss member, and FIG. 8 is a perspective view showing an example of the usage state of the mounting device according to the present invention. 1...Mounting device 2...Space equipment 3...
Engagement device 4... Gripping means 5... Space facility structure 8... Heat resistant panel 9... Truss member 2
4... Guide cone 30... Stopper 31.
... Guide pin 33 ... Guide part 35 ... Cylinder part 37 ... Coil spring 38 ... Cap plate 1st rA 23 Kaimata A 1st surface
3l-jl"id pin 24--D'()"]-n 32 Circle uL surface 25 Circle f1
Shu 33- f ite 26
Enzaishu, complainant P
34-7° roof 27 Subrinoku
35 Cylinder 28/Steel ball
36 Hole removal 30-stopper
37 Coil wire 38.
To Soar Alert Fig. 2 Fig. 3m Fig. 4 Fig. 5vA 8 (ml Kasu Iv Kasushi) ■ Fig. 6
Claims (1)
る係合手段と他方に配設される把持手段とからなり、前
記係合手段には電磁石となることのできる凸部を設ける
とともに、前記把持手段には電磁石となることができ、
かつ前記凸部を抱持することのできる凹部を設け、かつ
係合手段と把持手段の少なくとも一方に非電磁石状態に
おける両者の結合状態を維持できるストッパを設けたこ
とを特徴とする宇宙用機器の取付装置。It consists of an engaging means disposed on either one of the space equipment or the space facility structure and a gripping means disposed on the other, and the engaging means is provided with a convex portion that can serve as an electromagnet. , the gripping means can be an electromagnet;
and a recessed portion capable of holding the convex portion, and a stopper provided on at least one of the engaging means and the gripping means to maintain a coupled state between the two in a non-electromagnetic state. Mounting device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP60242880A JPS62103300A (en) | 1985-10-31 | 1985-10-31 | Fixture for space apparatus |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP60242880A JPS62103300A (en) | 1985-10-31 | 1985-10-31 | Fixture for space apparatus |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS62103300A true JPS62103300A (en) | 1987-05-13 |
Family
ID=17095603
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP60242880A Pending JPS62103300A (en) | 1985-10-31 | 1985-10-31 | Fixture for space apparatus |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS62103300A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0411600A (en) * | 1990-04-27 | 1992-01-16 | Natl Space Dev Agency Japan<Nasda> | Catching mechanism |
| JP2012507429A (en) * | 2008-11-04 | 2012-03-29 | テールズ | How to capture a container of planetary soil samples moving through outer space |
| JP2013203261A (en) * | 2012-03-28 | 2013-10-07 | Mitsubishi Heavy Ind Ltd | Spacecraft |
-
1985
- 1985-10-31 JP JP60242880A patent/JPS62103300A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0411600A (en) * | 1990-04-27 | 1992-01-16 | Natl Space Dev Agency Japan<Nasda> | Catching mechanism |
| JP2012507429A (en) * | 2008-11-04 | 2012-03-29 | テールズ | How to capture a container of planetary soil samples moving through outer space |
| JP2013203261A (en) * | 2012-03-28 | 2013-10-07 | Mitsubishi Heavy Ind Ltd | Spacecraft |
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