JPH03224899A - Satellite separation device - Google Patents
Satellite separation deviceInfo
- Publication number
- JPH03224899A JPH03224899A JP2018845A JP1884590A JPH03224899A JP H03224899 A JPH03224899 A JP H03224899A JP 2018845 A JP2018845 A JP 2018845A JP 1884590 A JP1884590 A JP 1884590A JP H03224899 A JPH03224899 A JP H03224899A
- Authority
- JP
- Japan
- Prior art keywords
- cable
- satellite
- latch
- cutter
- cut
- 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.)
- Granted
Links
- 238000000926 separation method Methods 0.000 title claims description 29
- 230000008878 coupling Effects 0.000 description 3
- 238000010168 coupling process Methods 0.000 description 3
- 238000005859 coupling reaction Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 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
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Installation Of Indoor Wiring (AREA)
- Flexible Shafts (AREA)
Abstract
Description
【発明の詳細な説明】
〔産業上の利用分野〕
本発明は、ケーブルを使用した作動保持機構を有する衛
星分離装置に関する。DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to a satellite separation device having an operation holding mechanism using a cable.
本出願人が出願中の衛星分離装置（特願平１１４４０９
５）について、第３図ないし第４図により説明する。Satellite separation device (patent application No. 114409) currently filed by the applicant
5) will be explained with reference to FIGS. 3 and 4.
第３図は衛星０１とロケット側である衛星分離装置体０
２との分離部（と同時に当接部でもある）近傍の図で（
ａ）はその平面図、（ｂ）はその側面図である。結合ボ
ルト／分離ナッ）０３が同上を４等分した各位置計４個
所に配設されて衛星０１と衛星分離部本体０２とを結合
しており、更にその外周側に各々ラッチ装置１が配設さ
れ、後述する、ラッチ装置１のフック３をケーブル１０
が衛星分離装置体０２側に固縛するような状態で引き付
けている。即ち、衛星分離装置はラッチ装置１とケーブ
ル１０とよりなり、ケーブル１０に対しては図示しない
別手段のケーブルカッタがケーブル１０を任意時期に切
断するよう最適の構成で衛星分離部本体０２に付設され
ている。Figure 3 shows satellite 01 and satellite separation device body 0 on the rocket side.
This is a diagram of the vicinity of the separation part (which is also the contact part at the same time) with 2 (
(a) is a plan view thereof, and (b) is a side view thereof. Coupling bolts/separation nuts) 03 are disposed at four positions in each of the four equal parts of the same, and connect the satellite 01 and the satellite separation part main body 02, and latch devices 1 are disposed on the outer periphery of each of them. The hook 3 of the latch device 1 is connected to the cable 10, which will be described later.
is drawn to the satellite separation device body 02 side in a secured manner. That is, the satellite separation device consists of a latch device 1 and a cable 10, and a cable cutter of another means (not shown) is attached to the satellite separation unit main body 02 in an optimal configuration so that the cable 10 can be cut at any time. has been done.
第４図は上記ラッチ装置１の詳細側面図である。FIG. 4 is a detailed side view of the latch device 1.
図において衛星Ｏ１と、ロケット側である衛星分離部本
体０２との分離面Ａの直下の衛星分離部本体０２の外周
にはブラケット４がスクリュウ付けされており、ブラケ
ット４には衛星分離部本体０２の機軸とほぼ垂直にピン
ポルト６が貫通しており、同ピンボルト６にはシーソー
状に回動可能にフック３が枢支されている。フック３は
分離面Ａに近い方の端部の外側、即ち衛星分離部本体０
２の機軸より見て遠い方の外側が、機軸とほぼ垂直な座
面であるフック係合圧３ａを有しており、後述のラッチ
アーム２のラッチ係合圧２ａと係合するように構成され
ている。フック３の他端側は機軸より見て外側に上記ケ
ーブル１０を係止するための窪みであるケーブル受３ｂ
を有していてケーブル１０を引掛けた際、滑らないよう
になっている。フック３よりは上記分離面Ａに近い位置
には、ブラケット４には上記ピンボルト６とほぼ平行な
ピンボルト５で回動可能に枢支されたラッチアーム２が
設けられており、フック３に近い方の側がフック３のフ
ック係合圧３ａと保合可能なラッチ係合圧２ａを有して
いて衛星０１と衛星分離部本体０２とが分離する迄は、
厳密にはケーブル１０が切断される迄は図示のようにフ
ック３のフック係合圧３ａと係合している。ラッチアー
ム２の他端は衛星０１側に屈曲してその先端に設けられ
た調整ポル）２ｂを介して衛星０１を機軸にほぼ平行に
抑え、衛星０１をロケット側である衛星分離部本体０２
に当接したまま固定している。ラッチアーム２には図示
のようにピンボルト５を軸としたトーションバネ８の一
端が引掛けられ、他端はブラケット４に引掛けられてい
てラッチアーム２を矢印Ｔ、の向き、即ち、調整ボルト
２ｂの設けられた端を衛星０１から離反させる向きに常
に回動させるように働いている。又、フック３にはピン
ボルト６を軸としたトーションバネ９の一端が引掛けら
れ、他端はブラケット４に引掛けられていてフック３を
矢印Ｔ２の向き、即ち、上記ラッチアーム２のラッチ係
合圧２ａからフック係合圧３ａを常に解放させる向きに
働いている。このトーションバネ９の働きはフック３の
ケーブル受３ａに引掛けられたケーブル１０の引張力に
よって拘束されている。In the figure, a bracket 4 is screwed onto the outer periphery of the satellite separation unit body 02 directly below the separation plane A between the satellite O1 and the satellite separation unit body 02 on the rocket side. A pin port 6 passes through the pin bolt 6 almost perpendicularly to the machine axis, and a hook 3 is pivotally supported on the pin bolt 6 so as to be rotatable in a seesaw manner. The hook 3 is attached to the outer side of the end near the separation plane A, that is, the satellite separation part main body 0.
The outer side farthest from the machine axis of 2 has a hook engagement pressure 3a which is a seating surface substantially perpendicular to the machine axis, and is configured to engage with the latch engagement pressure 2a of the latch arm 2, which will be described later. has been done. The other end of the hook 3 is a cable receiver 3b which is a recess for locking the cable 10 on the outside when viewed from the machine axis.
This prevents the cable 10 from slipping when hooked up. At a position closer to the separation surface A than the hook 3, the bracket 4 is provided with a latch arm 2 rotatably supported by a pin bolt 5 substantially parallel to the pin bolt 6. Until the side has a latch engagement pressure 2a that can maintain the hook engagement pressure 3a of the hook 3 and the satellite 01 and the satellite separation unit main body 02 are separated,
Strictly speaking, until the cable 10 is cut, it is engaged with the hook engaging pressure 3a of the hook 3 as shown in the figure. The other end of the latch arm 2 is bent toward the satellite 01 side, and holds the satellite 01 almost parallel to the axis via an adjustment pole (2b) provided at its tip.
It is fixed in contact with the As shown in the figure, one end of a torsion spring 8 with a pin bolt 5 as an axis is hooked to the latch arm 2, and the other end is hooked to a bracket 4, so that the latch arm 2 is oriented in the direction of arrow T, that is, the adjustment bolt It works to always rotate the end where 2b is provided in the direction to move away from the satellite 01. Also, one end of a torsion spring 9 with the pin bolt 6 as its axis is hooked on the hook 3, and the other end is hooked on the bracket 4, so that the hook 3 is oriented in the direction of arrow T2, that is, in the latch engagement of the latch arm 2. It always acts in a direction to release the hook engaging pressure 3a from the combined pressure 2a. The function of this torsion spring 9 is restrained by the tensile force of the cable 10 hooked on the cable receiver 3a of the hook 3.
以上において、衛星０１とともに発射されたロケットの
燃料が消尽すると用済みとなったロケットは衛星分離部
本体０２とともに衛星０１から分離される。そのため、
先ず、結合ボルト／分離ナツト０３の図示しない火工品
等が作動して結合ボルトの結合が開放される。４個所の
結合ボルトがすべて解放された後、今度は図示しないケ
ーブルカッタが作動してケーブル１０を切断する。する
と４個のラッチ装置１のフック３は同時に拘束を解かれ
てトーションバネ９により第４図の２点鎖線で示す位置
へ回動し、フック係合圧３ａがラッチアーム２のラッチ
係合圧２ａから外れる。すると、トーションバネ８のト
ルクによってラッチアーム２は図の２点鎖線の位置へ回
動し、衛星０１はすべて拘束を解かれる。次いで衛星分
離部本体０２はロケットとともにレトロスラストによっ
て静かに衛星０１より分離してゆく。In the above, when the fuel of the rocket launched together with the satellite 01 is exhausted, the spent rocket is separated from the satellite 01 together with the satellite separation unit main body 02. Therefore,
First, a pyrotechnic device (not shown) of the coupling bolt/separation nut 03 is activated to release the coupling bolt. After all four connecting bolts are released, a cable cutter (not shown) is operated to cut the cable 10. Then, the hooks 3 of the four latch devices 1 are simultaneously released and rotated by the torsion spring 9 to the position shown by the two-dot chain line in FIG. It deviates from 2a. Then, the latch arm 2 is rotated to the position indicated by the two-dot chain line in the figure by the torque of the torsion spring 8, and all of the satellites 01 are released from the restraint. Next, the satellite separation unit main body 02 is quietly separated from the satellite 01 by retrothrust together with the rocket.
〔発明が解決しようとする問題点１
上記本出願人の先出側に係るケーブルを使用した作動保
持機構を有する衛星分離装置では、ケーブルカッタ等に
よりケーブルを切断し、これにより保持機構が解除され
て、ラッチが解放されていた。しかし、ケープ切断によ
るケーブル飛散によりラッチ等へ、損傷をあたえる恐れ
があった。[Problem to be Solved by the Invention 1] In the above-mentioned satellite separation device that has an operation holding mechanism using a cable, which was proposed by the present applicant, the cable is cut with a cable cutter or the like, and the holding mechanism is thereby released. The latch was released. However, there was a risk of damage to the latch etc. due to the cable flying off when the cape was cut.
本発明は上記課題を解決するため次の手段を講する。 The present invention takes the following measures to solve the above problems.
すなわち、衛星分離装置として、衛星をロケット側に結
合分離するラッチ装置と、同ラッチ装置の作動を拘束ひ
るケーブルと、同ケーブルを切断するケーブルカッタと
を有する衛星分離装置において、上記ケーブルカッタ部
をよけてケーブルの切断部の両側に所定長のたわみケー
ブルを接続した。That is, in a satellite separation device that has a latch device that connects and separates a satellite to a rocket side, a cable that restricts the operation of the latch device, and a cable cutter that cuts the cable, the cable cutter section is used as a satellite separation device. A predetermined length of flexible cable was connected to both sides of the cut portion of the cable.
上記手段により、衛星分離時、ケーブルカッタでケーブ
ルが切断されたとき、ケーブルの切断部間はたわみケー
ブルで接続されているため、ケーブルが飛散することな
く保持されるとともに、ケーブルが所定量ゆるむことに
よりラッチ装置が作動して、衛星再分離される。このよ
うにしてラッチ装置等へ損傷をあたえる恐がなく、信頼
性が大幅に向上する。With the above means, when the cable is cut by a cable cutter during satellite separation, the cable is held without scattering and the cable is loosened by a predetermined amount since the cut parts of the cable are connected by a flexible cable. This activates the latch device and the satellite is reseparated. In this way, there is no risk of damage to the latch device, etc., and reliability is greatly improved.
本発明の一実施例を第１図と第２図より説明する。 An embodiment of the present invention will be explained with reference to FIGS. 1 and 2.
なお、従来例で説明した部分は、冗長さをさけるため説
明を省略し、この発明に関する部分を主体に説明する。Note that the description of the portions described in the conventional example will be omitted to avoid redundancy, and the description will mainly focus on the portions related to the present invention.
第１図にて、衛星０１はロケット側の衛星分離装置体０
２に、４個のラッチ装置１で結合される。またラッチ装
置１はケーブル１０でその作動が拘束されている。第２
図にケーブルカッタ１２部の詳細を示す。ケーブルカッ
タ１２の刃ａの部分をよけて、ケーブルカッタ１２の左
側近傍の２つ目のケーブルガイド１３ａの左側からケー
ブルカッタ１２の右側近傍の１つ目のケーブルガイド１
３ｃの右側の間のケーブル１０に、たわみケーブル１１
を接続する。たわみケーブル１１は所定長の長さを持ち
たわませるとともに、その中央部をケーブルガイド１３
ａのすぐ上に設けられたたわみケーブルガイド１４を通
して大きくたわまないようにしている。In Figure 1, satellite 01 is satellite separation device body 0 on the rocket side.
2 by four latching devices 1. Further, the operation of the latch device 1 is restricted by the cable 10. Second
The figure shows details of the cable cutter 12. Avoiding the blade a of the cable cutter 12, move from the left side of the second cable guide 13a near the left side of the cable cutter 12 to the first cable guide 1 near the right side of the cable cutter 12.
A flexible cable 11 is attached to the cable 10 between the right side of 3c.
Connect. The flexible cable 11 is bent to a predetermined length, and the center part is connected to the cable guide 13.
The flexible cable guide 14 provided just above the cable guide 14 prevents the cable from deflecting significantly.
以上の構成において、衛星を分離するとき、ケーブルカ
ッタ１２によりケーブル１０が切断されると、ケーブル
１０は所定量ゆるみ、ラッチ装置１の拘束を解放して、
衛星０１は分離される。このときケーブル１０の切断部
は両側でたわみケーブル１０により接続されているため
、飛散していて、付近のラッチ装置１等に損傷をあたえ
る恐れがなくなる。このようにして信軌性の高い衛星分
離装置かえられる。In the above configuration, when the cable 10 is cut by the cable cutter 12 when separating the satellite, the cable 10 is loosened by a predetermined amount, releasing the restraint of the latch device 1, and
Satellite 01 is separated. At this time, since the cut portion of the cable 10 is connected by the flexible cable 10 on both sides, there is no possibility that it will be scattered and damage the latch device 1 etc. in the vicinity. In this way, the satellite separation device with high reliability can be replaced.
以上に説明したように、本発明によれば、ケーブル切断
後のケーブルの脱落防止及びケーブル飛散によりラッチ
装置等へ損傷をあたえることを防止することができる。As described above, according to the present invention, it is possible to prevent the cable from falling off after the cable is cut and to prevent damage to the latch device or the like due to the cable scattering.
したがって衛星分離装置の信顛性を大幅に向上させるこ
とができる。Therefore, the reliability of the satellite separation device can be greatly improved.
第１図（ａ）図は本発明の一実施例の平面図、第１図（
ｂ）は同実施例の側面図、第２図は同実施例のケーブル
カッタ部の詳細図、第３図（ａ）は従来例の平面図、第
３図（ｂ）は同従来例の側面図、第４図は同実施例のラ
ッチ装置部の詳細図である。
１・・・ラッチ装置、０１・・・衛星。
１０・・・ケーブル、１１・・・たわみケーブル。
１２・・・ケーブルカッタ。FIG. 1(a) is a plan view of one embodiment of the present invention;
b) is a side view of the same embodiment, Fig. 2 is a detailed view of the cable cutter part of the same embodiment, Fig. 3(a) is a plan view of the conventional example, and Fig. 3(b) is a side view of the conventional example. 4 are detailed views of the latch device section of the same embodiment. 1... Latch device, 01... Satellite. 10... Cable, 11... Flexible cable. 12... Cable cutter.
Claims (1)
、同ラッチ装置の作動を拘束するケーブルと、同ケーブ
ルを切断するケーブルカッタとを有する衛星分離装置に
おいて、上記ケーブルカッタ部をよけてケーブルの切断
部の両側に所定長のたわみケーブルを接続してなること
を特徴とする衛星分離装置。In a satellite separation device that includes a latch device that connects and separates the satellite to the rocket side, a cable that restricts the operation of the latch device, and a cable cutter that cuts the cable, cutting the cable by avoiding the cable cutter part. A satellite separation device characterized in that a flexible cable of a predetermined length is connected to both sides of the satellite.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2018845A JP2634274B2 (en) | 1990-01-31 | 1990-01-31 | Satellite separation device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2018845A JP2634274B2 (en) | 1990-01-31 | 1990-01-31 | Satellite separation device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH03224899A true JPH03224899A (en) | 1991-10-03 |
| JP2634274B2 JP2634274B2 (en) | 1997-07-23 |
Family
ID=11982896
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP2018845A Expired - Fee Related JP2634274B2 (en) | 1990-01-31 | 1990-01-31 | Satellite separation device |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP2634274B2 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111470069A (en) * | 2020-04-08 | 2020-07-31 | 上海卫星工程研究所 | Lower end frame structure suitable for satellite bearing cylinder |
| CN112504032A (en) * | 2021-02-02 | 2021-03-16 | 星河动力(北京)空间科技有限公司 | Carrier rocket and cutting assembly for interstage separation of carrier rocket |
-
1990
- 1990-01-31 JP JP2018845A patent/JP2634274B2/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111470069A (en) * | 2020-04-08 | 2020-07-31 | 上海卫星工程研究所 | Lower end frame structure suitable for satellite bearing cylinder |
| CN111470069B (en) * | 2020-04-08 | 2021-11-16 | 上海卫星工程研究所 | Lower end frame structure suitable for satellite bearing cylinder |
| CN112504032A (en) * | 2021-02-02 | 2021-03-16 | 星河动力(北京)空间科技有限公司 | Carrier rocket and cutting assembly for interstage separation of carrier rocket |
| CN112504032B (en) * | 2021-02-02 | 2021-04-13 | 星河动力(北京)空间科技有限公司 | Carrier rocket and cutting assembly for interstage separation of carrier rocket |
Also Published As
| Publication number | Publication date |
|---|---|
| JP2634274B2 (en) | 1997-07-23 |
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