JPS63297200A - Artificial satellite separator - Google Patents
Artificial satellite separatorInfo
- Publication number
- JPS63297200A JPS63297200A JP62129393A JP12939387A JPS63297200A JP S63297200 A JPS63297200 A JP S63297200A JP 62129393 A JP62129393 A JP 62129393A JP 12939387 A JP12939387 A JP 12939387A JP S63297200 A JPS63297200 A JP S63297200A
- Authority
- JP
- Japan
- Prior art keywords
- satellite
- rocket
- artificial satellite
- separation device
- artificial
- 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 36
- 230000008878 coupling Effects 0.000 claims description 13
- 238000010168 coupling process Methods 0.000 claims description 13
- 238000005859 coupling reaction Methods 0.000 claims description 13
- 239000002360 explosive Substances 0.000 claims description 7
- 230000005540 biological transmission Effects 0.000 description 6
- 235000015842 Hesperis Nutrition 0.000 description 4
- 235000012633 Iberis amara Nutrition 0.000 description 4
- 238000004880 explosion Methods 0.000 description 4
- 230000000087 stabilizing effect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 1
- 239000000446 fuel Substances 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
- B64G1/645—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
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、人工衛星をロケットより分離し、宇宙空間に
放出きせる分離装置に関する。DETAILED DESCRIPTION OF THE INVENTION (Field of Industrial Application) The present invention relates to a separation device that separates an artificial satellite from a rocket and releases it into outer space.
（従来の技術）
従来、この種の分離装置においては、ロケットに電動モ
ータによって駆動するスピンテーブル機構が備えてあり
、このスピンテーブル上に衛星分離アダプタと衛星結合
分離部材とが装着してあり、人工衛星を回転（スピン）
させて分離していた。また、小型のロケットでは、人工
衛星とロケットとを衛星結合分離部材により分離するが
、その分離時の人工衛星に、回転（スピン）を与えるこ
とはできなかった。(Prior Art) Conventionally, in this type of separation device, a rocket is equipped with a spin table mechanism driven by an electric motor, and a satellite separation adapter and a satellite coupling separation member are mounted on this spin table. Rotate (spin) the satellite
It was separated. In addition, in small rockets, the satellite and the rocket are separated by a satellite coupling and separation member, but it is not possible to impart rotation (spin) to the satellite at the time of separation.
（発明が解決しようとする問題点）
ところが、前述した従来の分離装置の場合、人工衛星の
ロケットからの分離時において、人工衛星に回転力が加
わるので角運動量による人工衛星の姿勢安定は図れるが
、速度性分を与えることが出来ないので、ロケットの残
燃料等によって人工衛星とロケットとが衝突するおそれ
があった。(Problem to be Solved by the Invention) However, in the case of the conventional separation device described above, when the satellite is separated from the rocket, rotational force is applied to the satellite, so although it is possible to stabilize the satellite's attitude due to angular momentum, Since it is not possible to give a velocity component, there is a risk that the artificial satellite and the rocket will collide due to remaining fuel in the rocket.
また、小型ロケットや大型ロケットの側面に搭載した小
規模の人工衛星を分離する場合、単に分離スイッチによ
る方法で行なっていた。したがって、人工衛星は、回転
を通じて生じる角運動量による姿勢安定を得ることがで
きないという問題があった。In addition, when separating small-scale satellites mounted on the side of small rockets or large rockets, this was done simply by using a separation switch. Therefore, there is a problem in that the artificial satellite cannot obtain attitude stability due to the angular momentum generated through rotation.
（問題点を解決するための手段）
前述の問題点を解決するために本発明が提供する手段は
、ロケットに搭載された人工衛星を空間において当該ロ
ケットから分離する人工衛星分離装置におい工、スプリ
ングと、このスプリングの弾性力を回転力に変換しその
回転力を前記人工衛星に伝達する回転機構部と、前記ロ
ケットと前記人工衛星との結合をし衛星分離指令を受け
たときその結合を解く衛星結合分離部材とを備えている
ことを特徴とする。(Means for Solving the Problems) Means provided by the present invention in order to solve the above-mentioned problems is an artificial satellite separation device that separates an artificial satellite mounted on a rocket from the rocket in space, and a spring. a rotating mechanism unit that converts the elastic force of the spring into rotational force and transmits the rotational force to the artificial satellite; and a rotation mechanism unit that connects the rocket and the artificial satellite and releases the connection when a satellite separation command is received. A satellite coupling separation member.
（実施例） 次に、本発明について図面を参照して説明する。(Example) Next, the present invention will be explained with reference to the drawings.
第１図は本発明の人工衛星分離装置を示す縦断面図、第
２図〜第４＠は第１図の人工衛星分離装置を搭載したロ
ケットの一部を示す側面図、第５図は第１図の人工衛星
分離装置を搭載したロケットの内部を示す斜視図である
。FIG. 1 is a vertical cross-sectional view showing the satellite separation device of the present invention, FIGS. 2 to 4 are side views showing a part of the rocket on which the satellite separation device of FIG. FIG. 2 is a perspective view showing the inside of a rocket on which the satellite separation device of FIG. 1 is mounted.
図中、１は人工衛星、２はロケット、３は人工衛星の連
結部、４は爆発ボルト（衛星結合分離部材に対応する）
、５は回転体、５ａは回転伝達凸部、５ｂはネジ山、５
ｃは回転軸、６はフィルスプリング（スプリングに対応
する）、７はハウジング部、７ａはネジ溝、７ｂは結合
ボルト、８は人工衛星の回転軸、９は人工衛星分離装置
、１０は座金、１１は凹部である。In the figure, 1 is the satellite, 2 is the rocket, 3 is the satellite connection part, and 4 is the explosion bolt (corresponding to the satellite connection and separation member).
, 5 is a rotating body, 5a is a rotation transmission convex portion, 5b is a screw thread, 5
c is a rotating shaft, 6 is a fill spring (corresponding to a spring), 7 is a housing part, 7a is a screw groove, 7b is a coupling bolt, 8 is a rotating shaft of a satellite, 9 is a satellite separation device, 10 is a washer, 11 is a recessed portion.
人工衛星１は、第４図に示すように、ロケット２の先端
部に人工衛星分離装置９を介して搭載しである。また、
人工衛星１は、第１図、第２区、第５図に示すように、
様々な態様でロケット２に搭載される。As shown in FIG. 4, the artificial satellite 1 is mounted on the tip of a rocket 2 via an artificial satellite separation device 9. Also,
As shown in Fig. 1, Section 2, and Fig. 5, the artificial satellite 1 is
It is mounted on the rocket 2 in various ways.
人工衛星分離装置９は、コイルスプリング６と、このコ
イルスプリング６の弾性力又は伸張力を回転力に変換し
、かつその回転力を人工衛星１に伝達する回転機構部と
、口・ケラト２に対する人工衛星１の結合状態を解く衛
星結合分離部材４とコイルスプリング６を収容するハウ
ジング部７とを備えている。The satellite separation device 9 includes a coil spring 6, a rotation mechanism unit that converts the elastic force or extension force of the coil spring 6 into rotational force and transmits the rotational force to the satellite 1, and a rotation mechanism for the mouth/kerato 2. It includes a satellite coupling/separation member 4 for releasing the coupled state of the artificial satellite 1 and a housing part 7 for housing a coil spring 6.
コイルスプリング６はハウジング部７内に収縮させて収
容してあり、そのコイルスプリング６の一端部はハウジ
ング部７の底面部に固定されている。The coil spring 6 is contracted and housed in the housing part 7, and one end of the coil spring 6 is fixed to the bottom surface of the housing part 7.
ハウジング部７は、結合ボルト７ｂを用いてロケット２
に固定されている。ハウジング部７の開口部は人工衛星
１の結合部３により開本され、ハウジング部７と人工衛
星１の結合部３とは爆発ボルト４により結合きれている
。人工衛星１の結合部３には、回転体５の回転伝達凸部
５ａを嵌め込むための凹部１１が設けである。なお、爆
発ボルト４は遠隔起爆できる爆薬を内蔵するように設計
妨れたボルトで、内蔵爆薬の爆発によりボルトが切断あ
るいは溶断されるようになっている。The housing part 7 is attached to the rocket 2 using a connecting bolt 7b.
is fixed. The opening of the housing part 7 is opened by the connecting part 3 of the artificial satellite 1, and the housing part 7 and the connecting part 3 of the artificial satellite 1 are completely connected by an explosive bolt 4. The coupling portion 3 of the artificial satellite 1 is provided with a recess 11 into which the rotation transmission convex portion 5a of the rotating body 5 is fitted. The explosive bolt 4 is a bolt designed to contain an explosive that can be detonated remotely, and the bolt is cut or fused by the explosion of the built-in explosive.
回転機構部は、コイルスプリング６の伸張力を回転力に
変換して人工衛星を回転させる回転体５と、この回転体
５の軸８方向への運動を回転軸８を中心とするスムース
な回転運動に導くネジ溝（雌ねじ）７ａとからなる。The rotation mechanism unit includes a rotating body 5 that converts the tension force of a coil spring 6 into rotational force to rotate the satellite, and a rotating body 5 that converts the tension force of a coil spring 6 into rotational force to rotate the satellite, and a rotation mechanism that converts the movement of this rotating body 5 in the direction of an axis 8 into smooth rotation around the rotation axis 8. It consists of a threaded groove (female thread) 7a that leads to movement.
回転体５は全体が円盤状をなし、その周壁にはネジ山（
雄ネジ）５ｂが設けてあり、一方の端面（人工衛星１側
の面）には２個の回転伝達凸部５ａが設けてあり、他方
の端面（ロケット２側の面）には回転軸５ｃが設けであ
る。The rotating body 5 has a disk shape as a whole, and has screw threads (
A male thread) 5b is provided, two rotation transmission protrusions 5a are provided on one end surface (the surface on the satellite 1 side), and a rotation shaft 5c is provided on the other end surface (the surface on the rocket 2 side). is the provision.
回転体５は、コイルスプリング６に座金１０を介して回
転自在に連結しである。回転伝達凸部５ａは、回転体５
の回転力を人工衛星１の結合部３に伝達する。The rotating body 5 is rotatably connected to a coil spring 6 via a washer 10. The rotation transmission convex portion 5a is connected to the rotating body 5.
The rotational force is transmitted to the coupling part 3 of the artificial satellite 1.
ネジ溝７ａは、ハウジング部７の開口部近傍の内間壁に
設けてあり、回転体５のネジ山５ｂとかみ合う。The thread groove 7a is provided on the inner wall near the opening of the housing portion 7, and engages with the thread 5b of the rotating body 5.
ロケット２から人工衛星１を分離するには、爆発ボルト
４を遠隔起爆して切断あるいは溶断する。爆発ボルト４
が切断諮れるとロケット２に対する人工衛星１の結合状
態が解かれ、ハウジング部７内において収縮していたコ
イルスプリング６が伸張して回転体５を回転軸８の方向
に押し上げる。押し上げられた回転体５はそのネジ山５
ｂがハウジング部７のネジ溝７ａに導かれて回転する。To separate the satellite 1 from the rocket 2, the explosive bolt 4 is remotely detonated and cut or fused. explosive bolt 4
When the satellite 1 is disconnected from the rocket 2, the coil spring 6, which had been contracted within the housing section 7, expands and pushes the rotating body 5 toward the rotation axis 8. The pushed up rotating body 5 is its screw thread 5
b is guided by the screw groove 7a of the housing part 7 and rotates.
押し上げられながら回転する回転体５は、人工衛星１を
押し上げると同時に、回転伝達凸部５ａを通じて回転力
を与える。その結果、人工衛星１は回転しながら回転軸
８の方向に勢いよく放出きれる。The rotating body 5, which rotates while being pushed up, pushes up the satellite 1 and at the same time applies rotational force through the rotation transmission convex portion 5a. As a result, the artificial satellite 1 can be ejected with great force in the direction of the rotation axis 8 while rotating.
本実施例の人工衛星分離装置９によれば、コイルスプリ
ング６と、このコイルスプリング６の弾性力又は伸張力
を回転力に変換し、かつその回転力を人工衛星１に伝達
する回転機構部と、ロケット２に対する人工衛星１の結
合状態を解く衛星結合分離部材４とコイルスプリング６
を収容するハウジング部７を備えているので、分離時に
人工衛星１に回転力とその回転軸８の方向に飛ぶ力とを
与えることができ、人工衛星１の姿勢安定を得るととも
に、ロケット２との衝突や追突等を防ぐ：とができる。According to the satellite separation device 9 of this embodiment, the coil spring 6 and the rotation mechanism unit that converts the elastic force or extension force of the coil spring 6 into rotational force and transmits the rotational force to the artificial satellite 1 are provided. , a satellite coupling separation member 4 and a coil spring 6 for releasing the coupling state of the artificial satellite 1 to the rocket 2.
Since the housing part 7 that accommodates the rocket 2 is provided, it is possible to give the artificial satellite 1 a rotational force and a force to fly in the direction of its rotation axis 8 at the time of separation, thereby stabilizing the attitude of the artificial satellite 1 and also Preventing collisions and rear-end collisions: Can be done.
なお、前述の実施例においては、衛星結合分離部材の一
例として爆発ボルト４及びスプリングの一例としてコイ
ルスプリング６を用いた場合について述べたが、これに
代え他の部材又は他のスプリングを用いるようにしても
よい。In the above-mentioned embodiment, a case was described in which the explosion bolt 4 was used as an example of the satellite coupling and separation member and the coil spring 6 was used as an example of the spring, but other members or other springs may be used instead. It's okay.
（発明の効果）
以上説明したように本発明の人工衛星分離装置によれば
、分離時に人工衛星を回転させながら回転軸方向に勢゛
いよく放出することができるので、人工衛星の姿勢安定
を得るとともに、ロケットとの衝突や追突等を防ぎ得る
。(Effects of the Invention) As explained above, according to the artificial satellite separation device of the present invention, it is possible to forcefully eject the artificial satellite in the direction of the rotation axis while rotating the artificial satellite at the time of separation, thereby stabilizing the attitude of the artificial satellite. At the same time, collisions and rear-end collisions with rockets can be prevented.
第１図は本発明の人工衛星分離装置を示す縦断面図、第
２図〜第４図は第１図の人工衛星分離装置を搭載したロ
ケットの一部を示す側面図、第５図は第１図の人工衛星
分離装置を搭載したロケットの内部を示す斜視図である
。
１・・・人工衛星、２・・・ロケット、３・・・人工衛
星の連結部、４・・・爆発ボルト（衛星結合分離部材に
対応する）、５・・・回転体、５ａ・・・回転伝達凸部
、５ｂ・・・ネジ山、５Ｃ・・・回転軸、６・・・コイ
ルスプリング（スプリングに対応する）、７・・・ハウ
ジング部、７ａ・・・ネジ溝、７ｂ・・・結合ボルト、
８・・・人工衛星の回転軸、９・・・人工衛星分離装置
、１０・・・座金、１１・・・凹部。FIG. 1 is a longitudinal sectional view showing the satellite separation device of the present invention, FIGS. 2 to 4 are side views showing a part of a rocket carrying the satellite separation device of FIG. 1, and FIG. FIG. 2 is a perspective view showing the inside of a rocket on which the satellite separation device of FIG. 1 is mounted. DESCRIPTION OF SYMBOLS 1...Artificial satellite, 2...Rocket, 3...Artificial satellite connection part, 4...Explosion bolt (corresponding to the satellite coupling and separation member), 5...Rotating body, 5a... Rotation transmission convex portion, 5b... Thread thread, 5C... Rotating shaft, 6... Coil spring (corresponding to the spring), 7... Housing portion, 7a... Thread groove, 7b... connection bolt,
8... Rotation axis of the artificial satellite, 9... Artificial satellite separation device, 10... Washer, 11... Recessed portion.
Claims (3)
該ロケットから分離する人工衛星分離装置において、ス
プリングと、このスプリングの弾性力を回転力に変換し
その回転力を前記人工衛星に伝達する回転機構部と、前
記ロケットと前記人工衛星との結合をし衛星分離指令を
受けたときその結合を解く衛星結合分離部材とを備えて
いることを特徴とする人工衛星分離装置。(1) A satellite separation device that separates an artificial satellite mounted on a rocket from the rocket in space includes a spring and a rotation mechanism that converts the elastic force of the spring into rotational force and transmits the rotational force to the satellite. and a satellite coupling and separation member that couples the rocket and the artificial satellite and releases the coupling when a satellite separation command is received.
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。(2) The artificial satellite separation device according to claim 1, wherein the satellite connection separation member is an explosive bolt.
コイル状に巻かれてなり、前記ロケット本体の先端と前
記人工衛星との間に介在させてあることを特徴とする特
許請求の範囲第１項又は第２項記載の人工衛星分離装置
。(3) The spring is wound into a coil coaxially with the longitudinal axis of the rocket, and is interposed between the tip of the rocket body and the artificial satellite. The artificial satellite separation device according to item 1 or 2.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP62129393A JPS63297200A (en) | 1987-05-26 | 1987-05-26 | Artificial satellite separator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP62129393A JPS63297200A (en) | 1987-05-26 | 1987-05-26 | Artificial satellite separator |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS63297200A true JPS63297200A (en) | 1988-12-05 |
Family
ID=15008463
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP62129393A Pending JPS63297200A (en) | 1987-05-26 | 1987-05-26 | Artificial satellite separator |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS63297200A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS6428099A (en) * | 1987-07-23 | 1989-01-30 | Nec Corp | Artificial satellite separation system |
| JPH05162696A (en) * | 1991-12-11 | 1993-06-29 | Natl Space Dev Agency Japan<Nasda> | Micro-satellite launching system |
| JPH07132899A (en) * | 1993-11-09 | 1995-05-23 | Nec Eng Ltd | Shock absorbing structure and shock absorbing separation mechanism for artificial satellite |
-
1987
- 1987-05-26 JP JP62129393A patent/JPS63297200A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS6428099A (en) * | 1987-07-23 | 1989-01-30 | Nec Corp | Artificial satellite separation system |
| JPH05162696A (en) * | 1991-12-11 | 1993-06-29 | Natl Space Dev Agency Japan<Nasda> | Micro-satellite launching system |
| JPH07132899A (en) * | 1993-11-09 | 1995-05-23 | Nec Eng Ltd | Shock absorbing structure and shock absorbing separation mechanism for artificial satellite |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US6224013B1 (en) | Tail fin deployment device | |
| WO2007133247A9 (en) | Fin retention and deployment mechanism | |
| US4137848A (en) | Rocket engine mount | |
| US4646102A (en) | Deployable antenna reflector apparatus | |
| EP0292027A3 (en) | Piezoelectric fuse for projectile with safe and arm mechanism | |
| JPS63297200A (en) | Artificial satellite separator | |
| US3684214A (en) | Flying body having extensible fins | |
| US5271286A (en) | Spline screw multiple rotations mechanism | |
| US3757461A (en) | Impact-damage-resistant, propeller-driven toy | |
| US5159151A (en) | Missile nose fairing assembly | |
| US4352314A (en) | Device for releasably securing a coupling head to an external load mounted on an aircraft | |
| CN114735249B (en) | Locking and unlocking mechanism for satellite launching box | |
| US4726292A (en) | Fuse for sub-munitions to be expelled from a rocket | |
| JP4026793B2 (en) | Rocket motor | |
| US2918869A (en) | Gyroscope driving means | |
| US20200024002A1 (en) | Energy extraction and storage, and propulsion systems for space vehicles | |
| JPS63502171A (en) | spacecraft launcher | |
| US2967685A (en) | Pilot chute ejection device | |
| US5287810A (en) | Carrier shell ejecting a payload by means of a piston | |
| US3678859A (en) | Two stage impact fuze | |
| US3251024A (en) | Separable depth selection drive train | |
| US3228141A (en) | Toy rocket | |
| US4522103A (en) | Trap for an umbilical plug separated from a missile | |
| US4709586A (en) | Spring-driven gyroscope | |
| JPH0631346Y2 (en) | cracker |