JPS6154400A - Separator for artificial satellite - Google Patents
Separator for artificial satelliteInfo
- Publication number
- JPS6154400A JPS6154400A JP59175485A JP17548584A JPS6154400A JP S6154400 A JPS6154400 A JP S6154400A JP 59175485 A JP59175485 A JP 59175485A JP 17548584 A JP17548584 A JP 17548584A JP S6154400 A JPS6154400 A JP S6154400A
- Authority
- JP
- Japan
- Prior art keywords
- artificial satellite
- separation
- satellite
- artificial
- flight
- 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
- 238000000926 separation method Methods 0.000 claims description 35
- 230000001133 acceleration Effects 0.000 claims description 6
- 238000002347 injection Methods 0.000 claims description 3
- 239000007924 injection Substances 0.000 claims description 3
- 238000010586 diagram Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 239000003795 chemical substances by application Substances 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000018984 mastication Effects 0.000 description 1
- 238000010077 mastication Methods 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
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】
〔庄業上の利用分野〕
本発明は、人工衛星を飛行母体から分離する人工衛星分
離装置に関する。DETAILED DESCRIPTION OF THE INVENTION [Field of industrial application] The present invention relates to an artificial satellite separation device for separating an artificial satellite from a flight carrier.
従来、ロケットやスペース・シャトルなどの飛行母体か
ら人工衛星を分離するには、分離時及び分離後の姿勢を
安定させるため、まず、分離する前（ニガスジエツトや
モーターなどを使って、人工衛星に機軸方向を回転軸と
した回転連動を与え、その後に飛行母体（＝設けたスプ
リングなどの力によって人工衛星に機軸方向の直線運動
な与えて分離していた。このような従来の人工衛星分離
装置においては、人工衛星の分離に際して、回転連動を
与える分離用加速装置と直線連動を与える分離用加速装
置の両方が必要なので、装置全体が複雑（＝なるという
欠点があった。Conventionally, in order to separate an artificial satellite from a flight parent such as a rocket or space shuttle, in order to stabilize its attitude during and after separation, the satellite must first be pivoted before separation (using a jet or motor, etc.). A rotation axis is applied to the satellite, and then the satellite is separated by applying a linear motion in the direction of the aircraft axis using the force of a spring installed on the flight base.In such conventional satellite separation equipment, When separating an artificial satellite, both a separation accelerator that provides rotational interlocking and a separation accelerator that provides linear interlocking are required, so the entire device is complicated.
本発明の目的は、螺合装置と分離用加速装置とにより人
工衛星に直線連動と回転連動との両方を与えることによ
りジャイロ剛性による安定した姿勢を以て人工衛星を飛
行母体から分離できる人工衛星分離装置を提供すること
である。An object of the present invention is to provide an artificial satellite separation device that can separate an artificial satellite from a flight base with a stable attitude due to gyro rigidity by providing both linear interlocking and rotational interlocking to an artificial satellite using a screw coupling device and a separation accelerator. The goal is to provide the following.
本発明は、飛行母体（＝設けた人工衛星支持案内螺合装
置と、該系内螺合装置に対応適合する人工衛星に設けた
被案内螺合装置と、人工衛星（＝設けた前記飛行母体に
指間する分離用加速装置とにより構成される。The present invention relates to a flight carrier (=an artificial satellite support guide screwing device provided thereon, a guided screwing device provided on an artificial satellite that corresponds to the in-system screwing device, and an artificial satellite (=a said flight carrier provided). The system consists of a separation accelerator and a separation accelerator.
本発明の実施例について図面を参照して説明する。 Embodiments of the present invention will be described with reference to the drawings.
第１〜第４図において、人工衛星１内の雌孔部２には、
飛行母体乙に突出形成されるらせん体４が螺合している
。第１〜第６図においては、人工衛星１にジェット噴流
噴射装置によりｆ４成される分離用加速装置５が取り付
けられている。第４図（＝おいては、人工衛星１にバネ
加速装置により構成される分離用加速装置６が収り付け
られている。In FIGS. 1 to 4, the female hole 2 in the satellite 1 has
A spiral body 4 formed protruding from the flight base body B is screwed together. In FIGS. 1 to 6, a separation accelerator 5 configured by a jet jet injection device is attached to the artificial satellite 1. In FIG. 4, a separation accelerator 6 constituted by a spring accelerator is housed in the artificial satellite 1.
第５〜第８図において、飛行母体Ｚ内の雌孔部２には、
人工衛星８（＝突出形成されるらせん体４が螺合してい
る。第５〜第７図においては、人工衛星８にジェット噴
流噴射装置により構成される分離用加速装置５が取り付
けられている。第８図（＝おいては、人工衛星８（−バ
ネ加速装置（＝より構成される分離用加速装置６が取り
付けられている。In Figs. 5 to 8, the female hole 2 in the flight base Z has the following features:
Artificial satellite 8 (= spiral body 4 formed in a protruding manner is screwed together. In Figs. 5 to 7, a separation accelerator 5 constituted by a jet injection device is attached to the artificial satellite 8. In FIG. 8, a separation accelerator 6 consisting of an artificial satellite 8 (--spring accelerator (=) is attached.
第１〜第６図に示す第１の実施例の作動について説明す
る。The operation of the first embodiment shown in FIGS. 1 to 6 will be explained.
第１図の状態では、人工衛星１はらせん体４を設けた飛
行母体６（＝ねじ込まれた状態になっている。この状態
で分離用加速装置べ５を作動させると、ジェット噴流（
−よる推力によって、人工衛星１は飛行母体乙のらせん
体４に沿って、第２図に示すよう（＝らせん運動を始め
る。このようならせん運動を続（すた後に人工衛星１は
、飛行母体３のらせん体４から外れ、このようにして外
れた後の人工衛星１は、回転運動とともに回転軸方向へ
の直線連動を行なっている。この直線運動ζ二よって人
工衛星１は、第６図１＝示すように飛行体３から徐々（
＝離れて行って、この場合に分離した人工衛星１の姿勢
は回転Ｍ動のジャイロ剛性によって安定している。In the state shown in Fig. 1, the artificial satellite 1 is in a state where the flight base 6 (= screwed in) is provided with the spiral body 4. When the separation accelerator base 5 is operated in this state, a jet jet (
- With the thrust of The artificial satellite 1, which has come off the spiral body 4 of the base body 3, performs a rotational movement as well as a linear movement in the direction of the rotation axis. Due to this linear movement ζ2, the artificial satellite 1 Figure 1 = Gradually starting from the aircraft 3 as shown (
= In this case, the attitude of the separated artificial satellite 1 is stabilized by the gyro rigidity of the rotation M movement.
第４図（＝示す第２の実施例の作動について説明する。The operation of the second embodiment shown in FIG. 4 will be explained.
第２の′Ａ施例の人工衛星分離装置（＝おいて、分離用
加速装置６の作動（＝よって人工衛星１は、らせん体４
（＝そってらせん連動を始め、第１図の場合と同様に回
軸運動とともに直線連動をして、人工衛星１と飛行母体
３とが分離する。In the artificial satellite separation device of the second 'A embodiment (=, the operation of the separation accelerator 6 (=therefore, the artificial satellite 1
(=Spiral interlocking begins, and as in the case of Fig. 1, linear interlocking with rotational movement occurs, and the artificial satellite 1 and the flight base body 3 separate.
第５〜第７図（−示す第３の実施例の作動については、
第１〜第３図（＝示１３１の実施例の作動と同様である
。第８図（＝示す第４の実施例の作動については、第４
図に示す第２の実施例の作動と同様である。Regarding the operation of the third embodiment shown in Figs. 5 to 7 (-),
The operation of the fourth embodiment shown in FIGS. 1 to 3 (= is the same as that of the fourth embodiment shown in
The operation is similar to that of the second embodiment shown in the figure.
上記の例に示す人工衛星分離装置においては、加速度を
与える方向は必ずしも厳密に機軸方回に一致する必要は
無く、与えた加速度の主な部分がらせん方向の運動に有
効に使われるような方向であればよい。また、らせん状
雌孔部２も完全に連続したらせんである必要はなく、ら
せん連動が滑らかに行えるようなものであればよい。さ
らに摩擦の減少を図るために、らせん体４を螺合する部
分１：、しまやベアリングなどを使用しても何ら支障は
ない。In the satellite separation device shown in the example above, the direction in which the acceleration is applied does not necessarily have to correspond strictly to the direction of the axis, but rather the direction in which the main part of the applied acceleration is effectively used for movement in the spiral direction. That's fine. Further, the spiral female hole portion 2 does not need to be a completely continuous spiral, but may be one that allows smooth spiral interlocking. Furthermore, in order to reduce friction, there is no problem in using a striped bearing or the like in the part 1 where the spiral body 4 is screwed.
なお、上記の例による人工（Ｉ？ｊ星分離装置は、小型
の人工衛星を多数分離したり、親衛星から子衛星を分離
したりするのに適している。Note that the artificial (I?j star separation device) according to the above example is suitable for separating a large number of small artificial satellites or separating child satellites from a parent satellite.
〔発明の効果〕
本発明による人工衛星分離装置を使用することにより、
螺合装置と分離加速装置とにより人工衛星に直線運動と
ともに回転運動を与えて、人工衛星を飛行母体から分離
できる効果がある。[Effect of the invention] By using the artificial satellite separation device according to the present invention,
The screwing device and the separation accelerator provide linear motion as well as rotational motion to the artificial satellite, which has the effect of separating the artificial satellite from the flight base.
第１〜第６図は、それぞれ本発明による人工衛層分離装
置の第１の実施例における分離用加速装置の作動前、離
脱中、）咀祝後の状態を示す図、弗４図は本発明の第２
の実施例を示す構成図、第５〜第７図は、それぞれ本発
明の第３の実施例におＣする分離用加速装置の作動前、
離脱中、離脱後の状態を示す図、第８図は本発明の第４
の実施例を示す構成図である。
１・・・雌花部を設けた人工衛星、
２・・・雌花部、
３・・・らせん体を設けた飛行母体、
４・・・らせん体、
５．６・・・分離用加速装置、
７・・・雌花部を設けた飛行母体、
８・・・らせん体を設けた人工衛星。
特許出願人 日本ｍ気株式会社
・′−・〕
代理人 弁理士 円 原 １゛
８１、・
第１図 第２図 第３図
第４図
第５図 第６
」
づ
図
Ｂ
】Figures 1 to 6 are diagrams showing the states of the separation accelerator in the first embodiment of the artificial sanitary layer separation device according to the present invention before operation, during separation, and after mastication, respectively; Second invention
FIGS. 5 to 7 are block diagrams showing the third embodiment of the present invention, respectively, before operation of the separation accelerator according to the third embodiment of the present invention.
FIG. 8 is a diagram showing the state during and after detachment, and FIG.
FIG. DESCRIPTION OF SYMBOLS 1... Artificial satellite provided with a female flower part, 2... Female flower part, 3... Flight base body provided with a spiral body, 4... Spiral body, 5.6... Accelerator for separation, 7 ... A flying mother body with a female flower part, 8... An artificial satellite with a spiral body. Patent applicant Nippon Mki Co., Ltd.・'-・] Agent Patent attorney Yen Hara 1゛81,・Figure 1 Figure 2 Figure 3 Figure 4 Figure 5 Figure 6 Figure B]
Claims (1)
おいて、飛行母体には人工衛星支持案内螺合装置を設け
、人工衛星には該案内螺合装置に対応適合する被案内螺
合装置と飛行母体に指向して設けた分離用加速装置とを
有することを特徴とする人工衛星分離装置。 ２）前記飛行母体に設けた人工衛星支持案内螺合装置が
らせん体であり、前記人工衛星に設けた被案内螺合装置
が該らせん体に適合する螺設雌孔部であることを特徴と
する特許請求の範囲第１項記載の人工衛星分離装置。 ３）前記飛行母体に設けた人工衛星支持案内螺合装置が
螺設雌孔部であり、前記人工衛星に設けた被案内螺合装
置がらせん体であることを特徴とする特許請求の範囲第
１項記載の人工衛星分離装置。 ４）前記分離用加速装置がジェット噴流噴射装置である
ことを特徴とする特許請求の範囲第１項ないし第３項の
いずれか１項に記載の人工衛星分離装置。 ５）前記分離用加速装置がバネ加速装置であることを特
徴とする特許請求の範囲第１項ないし第３項のいずれか
１項に記載の人工衛星分離装置。[Claims] 1) In a separation device for separating an artificial satellite from a flight base, the flight base is provided with an artificial satellite support and guide screw device, and the artificial satellite is provided with a covering that corresponds to the guide screw device. An artificial satellite separation device characterized by having a guide screwing device and a separation acceleration device provided toward a flight base. 2) The artificial satellite support guide screwing device provided on the flight base is a spiral body, and the guided screwing device provided on the artificial satellite is a female screw hole that fits into the spiral body. An artificial satellite separation device according to claim 1. 3) The artificial satellite support guide screwing device provided on the flight base body is a screw female hole portion, and the guided screwing device provided on the artificial satellite is a spiral body. The artificial satellite separation device according to item 1. 4) The artificial satellite separation device according to any one of claims 1 to 3, wherein the separation acceleration device is a jet jet injection device. 5) The artificial satellite separation device according to any one of claims 1 to 3, wherein the separation acceleration device is a spring acceleration device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP59175485A JPS6154400A (en) | 1984-08-23 | 1984-08-23 | Separator for artificial satellite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP59175485A JPS6154400A (en) | 1984-08-23 | 1984-08-23 | Separator for artificial satellite |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS6154400A true JPS6154400A (en) | 1986-03-18 |
Family
ID=15996863
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP59175485A Pending JPS6154400A (en) | 1984-08-23 | 1984-08-23 | Separator for artificial satellite |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS6154400A (en) |
-
1984
- 1984-08-23 JP JP59175485A patent/JPS6154400A/en active Pending
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