JPS5939360B2 - Satellite separation device - Google Patents
Satellite separation deviceInfo
- Publication number
- JPS5939360B2 JPS5939360B2 JP51158293A JP15829376A JPS5939360B2 JP S5939360 B2 JPS5939360 B2 JP S5939360B2 JP 51158293 A JP51158293 A JP 51158293A JP 15829376 A JP15829376 A JP 15829376A JP S5939360 B2 JPS5939360 B2 JP S5939360B2
- Authority
- JP
- Japan
- Prior art keywords
- satellite
- artificial satellite
- artificial
- separation device
- accelerator
- 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.)
- Expired
Links
- 238000000926 separation method Methods 0.000 title claims description 22
- 230000033001 locomotion Effects 0.000 claims description 34
- 230000001133 acceleration Effects 0.000 description 2
- 230000007774 longterm Effects 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- 230000010006 flight Effects 0.000 description 1
- 239000003721 gunpowder Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 230000032258 transport 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
- B64G1/641—Interstage or payload connectors
- B64G1/643—Interstage or payload connectors for arranging multiple satellites in a single launcher
-
- 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
- B64G1/002—Launch systems
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
- B64G1/1085—Swarms and constellations
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
- Variable-Direction Aerials And Aerial Arrays (AREA)
Description
【発明の詳細な説明】
本発明は人工衛星分離装置に関し、特に人工衛星に回転
運動と回転軸方向への直線運動を与えて分離する人工衛
星分離装置に関する。DETAILED DESCRIPTION OF THE INVENTION The present invention relates to an artificial satellite separation device, and more particularly to an artificial satellite separation device that separates an artificial satellite by imparting a rotational motion and a linear motion in the direction of the rotation axis.
従来、回転運動により姿勢安定を保持するスピン安定型
人工衛星を、人工衛星を運搬する飛行体（たとえばロケ
ット）から分離する方法としては、まず、分離する前に
ガスジェットなどを使って飛行体の機軸方向を回転軸と
して全体に回転運動を与え、その後に飛行体に設けたス
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
動を与えて分離していた。Conventionally, the method of separating a spin-stabilized satellite, which maintains its attitude stability through rotational motion, from a flying vehicle (such as a rocket) that transports the satellite is to first use a gas jet or the like to stabilize the flying vehicle before separation. A rotational motion was applied to the entire satellite using the axis of rotation as the axis of rotation, and then a force such as a spring installed on the aircraft was used to apply a linear motion to the satellite in the direction of the axis to separate it.
また、回転運動を与えずに単にスプリングなどの力によ
り分離した場合は、回転運動を与えるためのガスジェッ
トなどの加速装置をあらかじめ人工衛星側に設けておき
、この加速装置を噴射して人工衛星を回転させる必要が
あった。In addition, if the separation is simply done by a force such as a spring without applying rotational motion, an accelerator such as a gas jet to provide rotational motion should be installed in advance on the satellite side, and this accelerator will be injected into the satellite. needed to be rotated.
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、回転運動を与える加速装置と直線運
動を与える加速装置の両方が必要であるので、装置全体
が複雑になるという欠点があった。Conventional satellite separation devices like this have the disadvantage that the entire device becomes complex because both an accelerator that provides rotational motion and an accelerator that provides linear motion are required to separate the satellites. .
さらに、このように、装置全体が複雑なために、多数の
人工衛星を１つの飛行体から分離するのは困難であると
いう欠点があった。Furthermore, since the entire device is complicated, it is difficult to separate a large number of satellites from one flying vehicle.
本発明の目的は、上記従来の欠点を除去するために、ら
せん状のガイドに人工衛星の嵌合部を嵌合し、この人工
衛星に回転運動と回転軸方向への直線運動を与えて分離
する人工衛星分離装置を提供することにある。In order to eliminate the above-mentioned drawbacks of the conventional art, an object of the present invention is to fit a fitting part of an artificial satellite into a spiral guide, give the artificial satellite a rotational motion and a linear motion in the direction of the rotation axis, and separate the satellite. The purpose of the present invention is to provide an artificial satellite separation device.
本発明は、らせん状のガイドが形成されている支持体と
、前記ガイドに嵌合する嵌合部が形成されている人工衛
星と、この人工衛星に回転運動を与えることによって回
転軸方向への直線運動により分離させるとともに該人工
衛星の姿勢を安定させる加速装置とを含むことを特徴と
する人工衛星分離装置を提供することにある。The present invention provides a support in which a spiral guide is formed, an artificial satellite in which a fitting part is formed to fit into the guide, and a rotational movement in the direction of the rotational axis by giving rotational motion to the artificial satellite. An object of the present invention is to provide an artificial satellite separation device characterized by including an accelerator that separates the artificial satellite by linear motion and stabilizes the attitude of the artificial satellite.
次に本発明の実施例について図面を参照して説明する。Next, embodiments of the present invention will be described with reference to the drawings.
第１図は第１実施例を示し、第１図人ないし第１図Ｃに
おいて、人工衛星１０の嵌合部１０ａには、支持体１１
に形成されているらせん状のガイド１１ａが嵌合してい
る。FIG. 1 shows a first embodiment, and in FIG. 1 to FIG.
A spiral guide 11a formed in is fitted.
このような人工衛星１０には、ジェットを利用した加速
装置１２が装着している。Such an artificial satellite 10 is equipped with an accelerator 12 that uses a jet.
上記構成の第１実施例の人工衛星分離装置においては、
第１図人は加速装置１２の作動前、第１図Ｂは加速装置
１２の作動中、第１図Ｃは人工衛星１０が支持体１１か
ら分離した後の状態を示している。In the artificial satellite separation device of the first embodiment having the above configuration,
FIG. 1 shows the person before the accelerator 12 is activated, FIG. 1B shows the accelerator 12 while it is in operation, and FIG.
このような第１図人の状態では、人工衛星１０はらせん
状のガイド１１ａを設けた支持体１１にねじ込まれた状
態になっている。In such a state as shown in FIG. 1, the artificial satellite 10 is screwed into the support 11 provided with the spiral guide 11a.
この状態で加速装置１２を作動させると、人工衛星１０
は支持体１１のらせんガイド１１ａに沿って第１図Ｂに
示すようにらせん運動を始める。When the accelerator 12 is activated in this state, the satellite 10
begins a helical movement along the helical guide 11a of the support 11 as shown in FIG. 1B.
このようならせん運動を続けた後に人工衛星１０は、支
持体１１のらせん状のガイド１１ａから外れ、このよう
にして外れた後の人工衛星１０には回転運動と回転軸方
向への直線運動がついている。After continuing such a spiral movement, the artificial satellite 10 comes off the spiral guide 11a of the support 11, and after being removed in this way, the artificial satellite 10 has a rotational movement and a linear movement in the direction of the rotation axis. Attached.
この直線運動により人工衛星１０は、支持体１１から徐
々に離れて行って、この場合に分離した後の人工衛星１
０の姿勢は第１図Ｃに示すように回転運動により安定し
ている。Due to this linear movement, the artificial satellite 10 gradually moves away from the support 11, and in this case, the artificial satellite 10 after separation
The posture of 0 is stabilized by rotational movement as shown in FIG. 1C.
第２図は第２実施例を示し、人工衛星１０の嵌合部１０
ａには、支持体１１に形成されているらせん状のガイド
１１ａが嵌合している。FIG. 2 shows a second embodiment, in which a fitting part 10 of an artificial satellite 10 is shown.
A spiral guide 11a formed on the support body 11 is fitted into the hole a.
このような人工衛星１０には、電磁モータの加速用電磁
コイル１３ａおよび１３ｂが配設され、また、支持体１
１には、電磁モータの加速用電磁コイル１３ｃおよび１
３ｄがそれぞれ配設されている。Such an artificial satellite 10 is provided with electromagnetic coils 13a and 13b for accelerating an electromagnetic motor, and a support 1
1 includes an electromagnetic coil 13c for accelerating the electromagnetic motor and a
3d are arranged respectively.
上記構成の第２実施例の人工衛星分離装置においては、
人工衛星１０が支持体１１のガイド１１ａを離れるに必
要な運動量を、電磁モータを使って徐々に加速して与え
ることができるので、第１図の場合と同様に人工衛星１
０は回転運動と直線運動を得て分離する。In the second embodiment of the satellite separation device having the above configuration,
Since the momentum necessary for the artificial satellite 10 to leave the guide 11a of the support 11 can be gradually accelerated using an electromagnetic motor, the artificial satellite 10 can be gradually accelerated as in the case of FIG.
0 obtains and separates rotational motion and linear motion.
したがって、人工衛星１０に衝撃を与えないで、分離す
ることが可能である。Therefore, it is possible to separate the artificial satellite 10 without giving any impact to it.
また、電磁モータは、ガスジェットや火薬に比べて取り
扱いや長期保存が容易である。Furthermore, electromagnetic motors are easier to handle and store for long periods of time than gas jets or gunpowder motors.
第３図は第３実施例を示し、人工衛星１０の嵌合部１０
ａには、支持体１１に形成されているらせん状のガイド
１１ａが嵌合し、このガイド１１ａは人工衛星１０側に
設けられ、１４は物質の爆発性を利用した加速装置を示
す。FIG. 3 shows a third embodiment, in which the fitting part 10 of the artificial satellite 10
A spiral guide 11a formed on the support body 11 is fitted into a, and this guide 11a is provided on the side of the artificial satellite 10, and 14 indicates an accelerator that utilizes the explosive properties of substances.
上記構成の第３実施例の人工衛星分離装置においては、
加速装置１４の作動によって人工衛星１０はらせん運動
を始め、第１図の場合と同様に人工衛星１０は回転運動
と直線運動を得て分離する。In the third embodiment of the satellite separation device having the above configuration,
Due to the operation of the accelerator 14, the artificial satellite 10 starts a spiral motion, and as in the case of FIG. 1, the artificial satellite 10 obtains rotational motion and linear motion and separates.
第４図は第４実施例を示し、人工衛星１０の嵌合部１０
ａには、支持体１１に形成されているらせん状のガイド
１１ａが嵌合している。FIG. 4 shows a fourth embodiment, in which the fitting part 10 of the artificial satellite 10
A spiral guide 11a formed on the support body 11 is fitted into the hole a.
これらの人工衛星１０と支持体１１との間には、スプリ
ングを利用した加速装置１５が装着しである。An accelerator device 15 using a spring is installed between these artificial satellites 10 and the support body 11.
この加速装置１５は、例えば、スプリングを圧縮した状
態でロックしておき、人工衛星１０の分離のときにロッ
クを解除し、スプリングが伸長する力を利用して人工衛
星１０に回転運動と直線運動を与えるようなものである
。For example, this accelerator 15 locks a spring in a compressed state, releases the lock when the satellite 10 is separated, and uses the force of the spring to expand to give the satellite 10 rotational and linear motion. It is like giving
上記構成の第４実施例の人工衛星分離装置において、加
速装置１５の作動によって人工衛星１０はらせん運動を
始め、第１図の場合と同様に回転運動と直線運動を得て
分離する。In the artificial satellite separation device of the fourth embodiment having the above configuration, the artificial satellite 10 starts a spiral motion by the operation of the accelerator 15, and is separated by obtaining rotational motion and linear motion as in the case of FIG.
このような第１実施例ないし第４実施例の人工衛星分離
装置においては、加速度を与える方向は必ずしも厳密に
らせん方向に一致する必要はなく、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。In the satellite separation devices of the first to fourth embodiments, the direction in which the acceleration is applied does not necessarily have to coincide strictly with the helical direction, and the main part of the applied acceleration is caused by the movement in the helical direction. Any direction is fine as long as it can be used effectively.
また、らせん状のガイド１１ａも完全に連続したらせん
である必要はなく、らせん運動が滑かに行えるようなも
のであればよい。Further, the spiral guide 11a does not need to be a completely continuous spiral, but may be one that allows smooth spiral movement.
さらに摩擦の減少を図るために、らせん状のガイド１１
ａに嵌合する部分に、こまやベアリングなどを使用して
も何ら支障はない。In order to further reduce friction, a spiral guide 11
There is no problem in using a top, bearing, etc. in the part that fits into a.
第５図は第５実施例を示し、複数個の人工衛星を分離す
る場合である。FIG. 5 shows a fifth embodiment, in which a plurality of artificial satellites are separated.
第５図において、人工衛星を運搬する飛行体であるロケ
ット２０に形成されている支持体２１には、衛星分離装
置２２および２３が装着しである。In FIG. 5, satellite separation devices 22 and 23 are attached to a support 21 formed on a rocket 20, which is a flying vehicle for transporting artificial satellites.
衛星分離装置２２には、人工衛星２４．２５が対になっ
て分離自在に嵌合し、また衛星分離装置２３には人工衛
星２６゜２７が対になって分離自在に嵌合している。A pair of artificial satellites 24 and 25 are fitted into the satellite separation device 22 in a separable manner, and a pair of artificial satellites 26 and 27 are fitted into the satellite separation device 23 in a separable manner.
このような状態を第５図において示し、この場合、人工
衛星２４．２５は分離した状態である。Such a situation is shown in FIG. 5, where the satellites 24, 25 are separated.
上記構成の第５実施例の人工衛星分離装置においては、
人工衛星２４，２５が対に、また人工衛星２６．２７も
対になっており、それぞれ対になっている人工衛星２４
．２５および２６．２７は反対の方向に加速され、反対
の方向にらせん運動を行なうにしたがって、人工衛星２
４．２５は、反対の方向に分離され、また、人工衛星２
６゜２７も反対の方向に分離される。In the artificial satellite separation device of the fifth embodiment having the above configuration,
The artificial satellites 24 and 25 are in a pair, and the artificial satellites 26 and 27 are also in a pair.
．． 25 and 26.27 are accelerated in opposite directions, and as they spiral in opposite directions, satellite 2
4.25 is separated in the opposite direction and also satellite 2
6°27 is also separated in the opposite direction.
この場合、分離された人工衛星２４，２５．２６および
２７が離れていく方向は、ロケット２０の支持体２１の
方向と直角であるので、ロケット２０の残留推力（ロケ
ットのエンジン燃焼停止後に残る僅かな推力）により該
ロケット２０が加速された場合でも、分離された人工衛
星と再衝突するおそれもない。In this case, the direction in which the separated satellites 24, 25, 26, and 27 move away is perpendicular to the direction of the support 21 of the rocket 20, so the residual thrust of the rocket 20 (the slight amount remaining after the rocket engine combustion stops) is perpendicular to the direction of the support 21 of the rocket 20. Even if the rocket 20 is accelerated by a large thrust force, there is no risk of colliding with the separated artificial satellite again.
したがって、このような第５実施例の人工衛星分離装置
によれば、人工衛星を分離させる方向がロケット２０を
運搬する飛行体の機軸方向のみならず、比較的自由に選
べる。Therefore, according to the artificial satellite separation device of the fifth embodiment, the direction in which the artificial satellite is separated can be selected relatively freely, not only in the direction of the axis of the aircraft carrying the rocket 20.
本発明は以上説明したように、単純な加速装置で人工衛
星に姿勢安定用の回転運動を与えて、比較的自由な方向
に分離できるので、小型の人工衛星を多数分離したり、
新衛星から小衛星を分離したりするのに適している。As explained above, the present invention uses a simple accelerator to give a satellite a rotational motion for attitude stabilization and can be separated in a relatively free direction.
Suitable for separating small satellites from new satellites.
また、電磁モータを使用すれば、長期間の保存に耐える
ので、長期間の飛行が必要な惑星間人工衛星などにおい
て小衛星を分離するのに有効であるなどの効果を有する
。Furthermore, if an electromagnetic motor is used, it can withstand long-term storage, so it is effective in separating small satellites in interplanetary satellites that require long-term flights.
第１図Ａ、Ｂ、Ｃおよび第２図ないし第５図は本発明に
係る人工衛星分離装置の第１ないし第５実施例の概略構
成説明図である。
１０．２４〜２７・・・・・・人工衛星、１１．２１・
・・・・・支持体、１１ａ・・・・・・ガイド、１２，
１４，１５・・・・・・加速装置、１３ａ〜１３ｄ・・
・・・・電磁コイル、２０・・・・・・ロケット、２２
，２３・・・・・・衛星分離装置。FIGS. 1A, B, and C and FIGS. 2 to 5 are schematic structural explanatory diagrams of first to fifth embodiments of the artificial satellite separation device according to the present invention. 10.24-27...Satellite, 11.21.
... Support body, 11a ... Guide, 12,
14, 15... Accelerator, 13a-13d...
... Electromagnetic coil, 20 ... Rocket, 22
, 23... Satellite separation device.
Claims (1)
ガイドに嵌合する嵌合部が形成されている人工衛星と、
この人工衛星に回転運動を与えることによって回転軸方
向への直線運動により分離させるとともに該人工衛星の
姿勢を安定させる加速装置とを含むことを特徴とする人
工衛星分離装置。1. A support body in which a spiral guide is formed, an artificial satellite in which a fitting part that fits into the guide is formed,
An artificial satellite separation device characterized by comprising: an accelerator that imparts rotational motion to the artificial satellite to separate it by linear movement in the direction of the rotational axis, and stabilizes the attitude of the artificial satellite.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP51158293A JPS5939360B2 (en) | 1976-12-28 | 1976-12-28 | Satellite separation device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP51158293A JPS5939360B2 (en) | 1976-12-28 | 1976-12-28 | Satellite separation device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS5383300A JPS5383300A (en) | 1978-07-22 |
| JPS5939360B2 true JPS5939360B2 (en) | 1984-09-22 |
Family
ID=15668431
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP51158293A Expired JPS5939360B2 (en) | 1976-12-28 | 1976-12-28 | Satellite separation device |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS5939360B2 (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2564734B (en) * | 2017-10-18 | 2019-07-10 | Ellinghaus Frank | Panelsat, an agile satellite with fuel free attitude control |
-
1976
- 1976-12-28 JP JP51158293A patent/JPS5939360B2/en not_active Expired
Also Published As
| Publication number | Publication date |
|---|---|
| JPS5383300A (en) | 1978-07-22 |
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| Vigneron et al. | Tether deployment and trajectory modeling for space plasma science missions | |
| Chilan et al. | Optimal low-thrust supersynchronous-to-geosynchronous orbit transfer | |
| Sawada et al. | Conceptual design of two-stage reusable launch systems using X-33 |