JPS58191700A - Separator for space missile - Google Patents
Separator for space missileInfo
- Publication number
- JPS58191700A JPS58191700A JP57075616A JP7561682A JPS58191700A JP S58191700 A JPS58191700 A JP S58191700A JP 57075616 A JP57075616 A JP 57075616A JP 7561682 A JP7561682 A JP 7561682A JP S58191700 A JPS58191700 A JP S58191700A
- Authority
- JP
- Japan
- Prior art keywords
- spacecraft
- separation
- separator
- present
- spin
- 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
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
- B64G1/645—Separators
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Storing, Repeated Paying-Out, And Re-Storing Of Elongated Articles (AREA)
- Transition And Organic Metals Composition Catalysts For Addition Polymerization (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (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】
本発明は人工衛星等宇宙飛行体をロケツ）または宇宙船
等の親機から分離する装置に関する。DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a device for separating a space vehicle such as an artificial satellite from a parent vehicle such as a rocket or spacecraft.
従来、スピン姿勢安定形の人工衛星等の宇宙飛行体をロ
ケットマたは宇宙船等から分離する方法としては、あら
かじめ親機にスピンを与えておいてから分離するか、分
離後にガスジェット等によりスピンを与えるかのいずれ
かの方法がとられてきた。 そのため、前者については
親機のシステムに負担を強い、まだ後者については分離
する宇宙飛行体側のシステムを複雑にしていた。Conventionally, the methods for separating a space vehicle such as a spin-attitude stable artificial satellite from a rocket or spacecraft include either giving a spin to the parent vehicle in advance and then separating it, or spinning it using a gas jet or the like after separation. One of two methods has been used: As a result, the former placed a burden on the system of the parent aircraft, while the latter complicated the system of the spacecraft that separated it.
本発明の目的は上記問題を解決した宇宙飛行体の分離装
置を提供することにある。An object of the present invention is to provide a spacecraft separation device that solves the above problems.
前記目的を達成するために、本発明による宇宙飛行体の
分離装置はロケットまたは宇宙船等の親機に設けられた
螺線状ガイドと、宇宙飛行体に設けられた嵌合部と、ス
プリングとからなり、前記螺線状ガイドに嵌合部を嵌合
させた状態で前記親機と宇宙飛行体とを引き離す方向に
付勢力を与え、分離時に前記宇宙飛行体にスピンを与え
るように構成しである。In order to achieve the above object, the spacecraft separation device according to the present invention includes a spiral guide provided on a parent vehicle such as a rocket or spacecraft, a fitting portion provided on the spacecraft, and a spring. and is configured to apply a biasing force in a direction to separate the parent aircraft and the spacecraft when the fitting portion is fitted to the spiral guide, and to impart spin to the spacecraft when separated. It is.
前記構成によれば、親機側あるいは宇宙飛行体側のシス
テムを従来より単純化でき、本発明の目的を完全に達成
することができる。According to the above configuration, the system on the base unit side or the spacecraft side can be simplified compared to the conventional system, and the object of the present invention can be completely achieved.
以下、図面等を参照して本発明をさらに詳しく説明する
。Hereinafter, the present invention will be explained in more detail with reference to the drawings and the like.
第１図は本発明による分離装置の一実施例を示す概略図
で、同図囚は分離前の状態を示した図１同図Ｃｏ）は分
離後の状態を示し九図、同図０３）は分離過程の状態を
示した図である。Fig. 1 is a schematic diagram showing an embodiment of the separation device according to the present invention. Fig. 1 shows the state before separation, Fig. 1 shows the state after separation, and Fig. 9 shows the state after separation. is a diagram showing the state of the separation process.
図において１は人工衛星等の宇宙飛行体１４は宇宙飛行
体の一面に形成された嵌合部、２はロケットまたは宇宙
船等の親機、３は親機２の一面に機械的に結合１７てい
る螺線状のガイドである。 親機２と飛行体１はこの螺
線状のガイド３と嵌合部４との嵌合により一体となって
いる。In the figure, 1 is a spacecraft such as an artificial satellite 14 is a fitting part formed on one side of the spacecraft, 2 is a base unit such as a rocket or spacecraft, and 3 is a mechanically coupled part 17 to one side of the base unit 2. It is a spiral guide. The base aircraft 2 and the flying object 1 are integrated by fitting the spiral guide 3 and the fitting portion 4 together.
親機２と飛行体１との間にはスプリング５が圧縮されて
挿入されてレリ、親機２と飛行体１とは常に離れる方向
に付勢力が与えちれている。A spring 5 is compressed and inserted between the base machine 2 and the flying object 1, so that a biasing force is always applied to the base machine 2 and the flying body 1 in the direction of separating them.
固定具６はこれら親機２と飛行体１とを機械的に固定し
ておくためのものである〕
第１図ｆ〜の状態に訃いて、ト述の固定具６が解除され
るとスプリング５の伸展力により第１図の）の矢印ａ方
向に飛行体１は押される。The fixing device 6 is for mechanically fixing the base aircraft 2 and the flying object 1.] When the fixing device 6 mentioned above is released in the state shown in FIG. Due to the extension force 5, the flying object 1 is pushed in the direction of the arrow a in Fig. 1).
このときａ方向に与えられる力の分力によシガイド３を
軸に、円周方向にも力が加わるだめ飛行われるため地上
において同じ機構でスピン運動発生させるより容易であ
る。 第１図（０）に示すようにガイド３と嵌合部４が
完全に離れたときには矢印すに示す十分々回転運動が与
えられており、スピンが掛けられた安定した姿勢で親１
機２から分離される。At this time, the component of the force applied in the direction a causes a force to be applied in the circumferential direction around the guide 3, causing the robot to fly, which is easier than generating a spin motion using the same mechanism on the ground. As shown in FIG. 1 (0), when the guide 3 and the fitting part 4 are completely separated, they have been given sufficient rotational movement as shown by the arrows, and the parent 1 is in a stable position with spin.
Separated from machine 2.
本実施例ではスプリング、固定金具は第１図に示すよう
な形状および個数を使用しているが１本発明はそれらに
限定されるものではなく、その機能を発揮できるものな
らば他の形状、数量等であっても良い。In this embodiment, the shape and number of springs and fixtures shown in FIG. It may be a quantity, etc.
以上、詳しく説明したように、本発明による分離装置は
従来より簡易な構成で宇宙飛行体をスピン姿勢安定した
状態で分離することができる。 しだがって、親機側お
よび宇宙飛行体側とも従来のように複雑な構成となるこ
とは々い。As described above in detail, the separation device according to the present invention can separate a spacecraft in a stable spin attitude with a simpler configuration than the conventional one. Therefore, both the base aircraft side and the spacecraft side often have complicated configurations as in the past.
本発明による分離装置は、比較的小形の宇宙飛行体を分
離する場合に、特に複数個分離する場合に適している。The separation device according to the present invention is suitable for separating relatively small spacecraft, particularly for separating a plurality of spacecraft.
第１図は本発明による宇宙飛行体の分離装置の一実施例
を説明するための概略図である。
１・・・人工衛星等の宇宙飛行体
２・・・ロケットｔたは宇宙船等の親機３・・・螺線状
ガイド ４・・・嵌合部５・・・スプリング ６
・・・固定具特許出願人 日本電気株式会社FIG. 1 is a schematic diagram for explaining an embodiment of a spacecraft separation device according to the present invention. 1... Space vehicle such as an artificial satellite 2... Base unit of a rocket or spacecraft 3... Spiral guide 4... Fitting portion 5... Spring 6
... Fixture patent applicant NEC Corporation
Claims (1)
ドと１宇宙飛行体に設けられた嵌合部と、スプリングと
からなり、前記螺線状ガイドに嵌合部を嵌合させた状態
で前記親機と宇宙飛行体とを引き離す方向に付勢力を与
え、分離時に前記宇宙飛行体にスピンを与えることを特
徴とする宇宙飛行体の分離装置。A rocket consists of a spiral guide provided on a parent machine such as a spacecraft, a fitting portion provided on a spacecraft, and a spring, and the fitting portion is fitted into the spiral guide. A separation device for a spacecraft, characterized in that a biasing force is applied in a direction to separate the parent aircraft and the spacecraft when the spacecraft is in a state of separation, and spin is imparted to the spacecraft when the spacecraft is separated.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP57075616A JPS58191700A (en) | 1982-05-06 | 1982-05-06 | Separator for space missile |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP57075616A JPS58191700A (en) | 1982-05-06 | 1982-05-06 | Separator for space missile |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS58191700A true JPS58191700A (en) | 1983-11-08 |
Family
ID=13581310
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP57075616A Pending JPS58191700A (en) | 1982-05-06 | 1982-05-06 | Separator for space missile |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS58191700A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0452999U (en) * | 1990-09-13 | 1992-05-06 | ||
| US11623771B2 (en) | 2018-04-16 | 2023-04-11 | Israel Aerospace Industries Ltd. | Nano-satellite |
-
1982
- 1982-05-06 JP JP57075616A patent/JPS58191700A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0452999U (en) * | 1990-09-13 | 1992-05-06 | ||
| US11623771B2 (en) | 2018-04-16 | 2023-04-11 | Israel Aerospace Industries Ltd. | Nano-satellite |
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