JP2609729B2 - Combination / separation method between satellite and rocket and apogee kick engine - Google Patents
Combination / separation method between satellite and rocket and apogee kick engineInfo
- Publication number
- JP2609729B2 JP2609729B2 JP1286083A JP28608389A JP2609729B2 JP 2609729 B2 JP2609729 B2 JP 2609729B2 JP 1286083 A JP1286083 A JP 1286083A JP 28608389 A JP28608389 A JP 28608389A JP 2609729 B2 JP2609729 B2 JP 2609729B2
- Authority
- JP
- Japan
- Prior art keywords
- satellite
- rocket
- apogee
- engine
- kick engine
- 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 - Fee Related
Links
- 238000000926 separation method Methods 0.000 title claims description 27
- 238000000034 method Methods 0.000 claims description 3
- 238000004880 explosion Methods 0.000 description 7
- 238000007796 conventional method Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 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
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
-
- 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
- B64G1/6455—Pyrotechnics; Using heat
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
- Braking Arrangements (AREA)
Description
【発明の詳細な説明】 〔産業上の利用分野〕 この発明は，静止衛星が，打上げロケツトによつて，
トランスフアー軌道に投入された後のロケツトの分離，
およびアポジ・キツク・エンジンによつて静止軌道に投
入された後のアポジ・キツク・エンジンの分離におい
て，信頼性の高い分離方法に関するものである。DETAILED DESCRIPTION OF THE INVENTION [Industrial field of application] The present invention relates to a geostationary satellite that uses a launch rocket to
Separation of the rocket after being put into the transfer orbit,
Also, the present invention relates to a highly reliable separation method for separating an apogee kick engine after being put into a geostationary orbit by an apogee kick engine.
第５図は，従来の衛星とロケツトおよびアポジ・キツ
ク・エンジンとの結合／分離方法を示す図であり，図に
おいて衛星（１）とアポジ・キツク・エンジン（２）は
分離ボルト（4a）により結合され，アポジ・キツク・エ
ンジン（２）とペイロード・アタツチ・フイツテイング
（３）は分離ボルト（4b）により結合されている。FIG. 5 is a diagram showing a conventional method of connecting / separating a satellite to a rocket and an apogee kick engine. In the figure, the satellite (1) and the apogee kick engine (2) are separated by a separation bolt (4a). The combined apogee kick engine (2) and payload attache fitting (3) are connected by a separation bolt (4b).
第６図は，上記（4a）および（4b）に示す分離ボルト
部の詳細を示す図であり衛星（１）側フランジ部とアポ
ジ・キツク・エンジン（２）側フランジ部が爆発ボルト
（7a）とアポジ・キツク・エンジン（２）に取付けられ
たナツト型火工品（8a）を用いて，ともじめされてい
る。また，アポジ・キツク・エンジン（２）側フランジ
部とペイロード・アタツチ・フイツテイング（３）側フ
ランジが爆発ボルト（7b）とペイロード・アタツチ・フ
イツテイング（３）に取付けられたナツト型火工品（8
b）を用いて，ともじめされている。FIG. 6 is a view showing details of the separation bolts shown in the above (4a) and (4b). The satellite (1) side flange and the apogee kick engine (2) side flange are explosion bolts (7a). And a nut-type pyrotechnic (8a) attached to the Apogee-Kick engine (2). In addition, a nut-type pyrotechnic (8) in which the flange part on the apogee-kit engine (2) and the payload-attaching-fitting (3) are attached to the explosion bolt (7b) and the payload-attaching-fitting (3)
It is bullied using b).
従来の衛星とロケットおよびアポジ・キツク・エンジ
ンとの結合は，上記のように構成され，衛星（１）がロ
ケツト（５）によりトランスフアー軌道に投入された
後，ペイロード・アタツチ・フイツテイング（３）に取
付けられたナツト型火工品（8b）が作動して爆発ボルト
（7b）が外れ，ボルト・キヤツチヤー（9b）で保持され
ることで，ペイロード・アタツチ・フイツテイング
（３）およびロケツト（５）の分離がなされ，さらにア
ポジ・キツク・エンジン（２）の推力により，静止軌道
に投入された後，アポジ・キツク・エンジン（２）に取
付けられたナツト型火工品（8a）が作動して爆発ボルト
（7a）が外れ，（9a）のボルト・キヤツチヤーで保持さ
れることで，衛星（１）からアポジ・キツク・エンジン
（２）の分離がなされていた。The combination of the conventional satellite with the rocket and the apogee kick engine is configured as described above, and after the satellite (1) is put into the transfer orbit by the rocket (5), the payload attack fitting (3) The nut-type pyrotechnic (8b) attached to the box operates and the explosion bolt (7b) comes off and is held by the bolt catcher (9b), so that the payload attachment fitting (3) and the rocket (5) After being put into geosynchronous orbit by the thrust of the Apogee-Kick engine (2), the nut type pyrotechnic (8a) attached to the Apogee-Kick engine (2) operates. The apogee kick engine (2) was separated from the satellite (1) by removing the explosion bolt (7a) and holding it with the bolt catcher of (9a).
上記のような従来の衛星とロケツトおよびアポジ・キ
ツク・エンジンの分離／結合方法では，衛星／アポジ・
キツク・エンジンの結合部は，大きなロケツト推力によ
つて生じた衛星からの荷重を伝達する機能と分離機能を
併せもち，アポジ・キツク・エンジン／ペイロード・ア
タツチ・フイツテイングの結合部は，大きなロケツト推
力によつて生じた衛星およびアポジ・キツク・エンジン
からの荷重を伝達する機能と分離機能を併せもつ必要が
あるため，両結合部ともに，分離ボルトが使われてい
る。In the conventional method for separating / combining the rocket and the apogee kick engine with the conventional satellite, the satellite / apogee
The joint of the kick engine has both the function of transmitting the load from the satellite generated by the large rocket thrust and the separation function, and the joint of the apogee kick engine / payload attack fitting has the large rocket thrust. It is necessary to have both the function of transmitting the load generated by the satellite and the load from the apogee kick engine and the separation function, so separation bolts are used for both joints.
分離ボルトを用いた分離動作が２回あるため,1回に比
べて分離失敗の確率が２倍になり，信頼性上の問題があ
つた。Since the separation operation using the separation bolt is performed twice, the probability of separation failure is doubled as compared with the case of one time, and there is a problem in reliability.
この発明は，かかる問題点を解決するためになされた
もので，分離ボルトを用いた分離回数を減らし，分離動
作を信頼性を上げることを目的とする。The present invention has been made to solve such a problem, and has as its object to reduce the number of times of separation using a separation bolt and increase the reliability of the separation operation.
この発明にかかわる衛星とロケツトおよびアポジ・キ
ツク・エンジンとを結合／分離方法は，衛星とアポジ・
キツク・エンジンおよびペイロード・アタツチ・フイツ
テイングを同一の分離ボルトにより結合し，アポジ・キ
ツク・エンジンと衛星を簡単なラツチ機構により，結合
するようにしたものである。The method for combining / separating a satellite and a rocket and an apogee kick engine according to the present invention is described below.
The kick engine and the payload attachment are connected by the same separation bolt, and the apogee kick engine and the satellite are connected by a simple latch mechanism.
この発明においては，衛星はロケツトによつてトラン
スフアー軌道に到達後，分離ボルトを外して，ロケツト
およびペイロード・アタツチ・フイツテイングを分離し
た後アポジ・キツク・エンジンと衛星はラツチ機構で結
合された状態で，アポジ・キツク・エンジンの推力で飛
行を続け，静止軌道に到着後，ラツチを外して，アポジ
・キツク・エンジンを分離することができる。アポジ・
キツク・エンジンの推力は小さいため，アポジ・キツク
・エンジン／衛星の結合は簡単なラツチ機構で荷重伝達
および分離が可能となる。According to the present invention, the satellite arrives at the transfer orbit by the rocket, and then the separation bolt is removed to separate the rocket and the payload attachment. After that, the apogee kick engine and the satellite are connected by a latch mechanism. Then, the flight can be continued with the thrust of the apogee kick engine, and after arriving in geosynchronous orbit, the latch can be removed to separate the apogee kick engine. Apogee
Since the thrust of the kick engine is small, the apogee kick engine / satellite combination can transmit and separate loads with a simple latch mechanism.
第１図は，この発明の一実施例を示す図であり，
（１）〜（５）は上記従来装置と全く同一ものもであ
る。簡単なラツチ機構（６）によつて衛星（１）とアポ
ジ・キツク・エンジン（２）が結合されている。FIG. 1 is a diagram showing one embodiment of the present invention.
(1) to (5) are exactly the same as the above-mentioned conventional apparatus. The satellite (1) and the apogee kick engine (2) are connected by a simple latch mechanism (6).
第２図は，上記分離ボルト部（４）の詳細を示す図で
あり，衛星（１）側フランジ部とアポジ・キツク・エン
ジン（２）のフランジ部およびペイロード・アタツチ・
フイツテイング（３）のフランジ部が，爆発ボルト
（７）とペイロード・アタツチ・フイツテイング（３）
に取付けられたナツト型火工品（８）を用いて，ともじ
めされている。FIG. 2 is a view showing the details of the separation bolt (4). The flange on the satellite (1) side, the flange of the apogee kick engine (2), and the payload attach.
The flange of the fitting (3) consists of an explosion bolt (7) and a payload attachment fitting (3).
It is ignited using a nut-type pyrotechnic (8) attached to the car.
第３図，第４図は，上記ラツチ機構部（６）の詳細を
示す図であり，衛星（１）側フランジ部とアポジ・キツ
ク・エンジン（２）のフランジ部が，ラツチ回転ピン
（11）を中心に回転するラツチ（10）がラツチ・ストツ
パー（12）にひつかけられることで結合する。第３図は
結合した状態を示し，第４図は結合していない状態を示
す。FIGS. 3 and 4 show the details of the latch mechanism (6). The flange of the satellite (1) and the flange of the apogee kick engine (2) are connected to the latch rotating pin (11). The latch (10) rotating around the bracket (10) is hooked to the latch / stopper (12) to join together. FIG. 3 shows a connected state, and FIG. 4 shows a non-connected state.
上記のように構成された衛星とロケツトおよびアポジ
・キツク・エンジンとの結合方法では，衛星（１）がロ
ケツト（５）によつてトランスフアー軌道に投入された
後，ペイロード・アタツチ・フイツテイング（３）に取
付けられたナツト型火工品（８）が作動して爆発ボルト
が外れ，ボルト・キヤツチヤー（９）で保持されること
で，ペイロード・アタツチ・フイツテイング（３）およ
びロケツト（５）の分離がなされ，衛星（１）はラツチ
機構（６）によりアポジ・キツク・エンジン（３）と結
合状態でアポジ・キツク・エンジン（３）の推力により
静止軌道に投入され，しかる後，ラツチ（10）をラツチ
・ストツパー（12）から外すことで，ラツチ機構（６）
を外し，アポジ・キツク・エンジン（２）を分離するこ
とになる。In the method of coupling the satellite and the rocket and the apogee kick engine configured as described above, after the satellite (1) is put into the transfer orbit by the rocket (5), the payload attaches to the satellite (1). The nut-type pyrotechnic (8) attached to () is actuated and the explosion bolt is released and held by the bolt catcher (9), thereby separating the payload attack fitting (3) and the rocket (5). The satellite (1) is put into geosynchronous orbit by the thrust of the apogee kick engine (3) in a state of being connected to the apogee kick engine (3) by the latch mechanism (6), and then the latch (10) The latch mechanism (6) can be removed from the latch / stopper (12).
To separate the apogee kick engine (2).
この発明は以上説明したとおり，ロケツト側ペイロー
ド・アタツチ・フイツテイング，アポジ・キツク・エン
ジンおよび衛星とを共通の分離ボルトで結合し，さらに
衛星とアポジ・キツク・エンジンとをラツチ機構で結合
し，上記衛星がロケツトによつてトランスフアー軌道に
投入された後，上記分離ボルトを外してロケツトおよび
ペイロード・アタツチ・フイツテイングを分離し，ロケ
ツト分離後，衛星はラツチ機構によりアポジ・キツク・
エンジンと結合状態で，アポジ・キツク・エンジンの推
力により静止軌道に投入され，しかる後上記ラツチ機構
を外し，アポジ・キツク・エンジンを衛星より分離する
ようにしたので，分離ボルトを用いた分離動作が従来の
２回から１回に減ることにより，分離動作の信頼性が向
上するという効果がある。As described above, according to the present invention, the rocket-side payload attachment, the apogee kick engine and the satellite are connected by a common separation bolt, and the satellite and the apogee kick engine are connected by a latch mechanism. After the satellite is put into the transfer orbit by the rocket, the above-mentioned separation bolt is removed to separate the rocket and the payload attach / fighting. After the rocket is separated, the satellite uses the latch mechanism to apply the apogee / kick.
In the combined state with the engine, it is put into geosynchronous orbit by the thrust of the Apogee-Kick engine, and then the latch mechanism is removed and the Apogee-Kick engine is separated from the satellite. Is reduced from two times to one time in the prior art, which has the effect of improving the reliability of the separation operation.
第１図はこの発明の一実施例を示す図，第２図はこの発
明による分離ボルト部の構造例を示す図，第３図および
第４図はこの発明によるラツチ機構を示す図，第５図は
従来の衛星とロケツトおよびアポジ・キツク・エンジン
との結合／分離方法を示す図，第６図は従来例における
分離ボルト部の構造例を示す図である。 図において，（１）は衛星，（２）はアポジ・キツク・
エンジン，（３）はペイロード・アタツチ・フイツテイ
ング，（４）は分離ボルト，（５）はロケツト，（６）
はラツチ機構，（７）は爆発ボルト，（８）はナツト型
火工品，（９）はボルトキヤツチヤー，（10）はラツ
チ，（11）はラツチ回転ピン，（12）はラツチ・ストツ
パーである。 尚，各図中同一符号は同一または相当部分を示す。FIG. 1 is a view showing an embodiment of the present invention, FIG. 2 is a view showing an example of the structure of a separation bolt portion according to the present invention, FIGS. 3 and 4 are views showing a latch mechanism according to the present invention, FIG. The figure shows a conventional method of connecting / separating a satellite to a rocket and an apogee kick engine. FIG. 6 is a view showing an example of the structure of a conventional separation bolt portion. In the figure, (1) is a satellite, (2) is an apogee kick,
Engine, (3) payload attack fitting, (4) separation bolt, (5) rocket, (6)
Is a latch mechanism, (7) is an explosion bolt, (8) is a nut type pyrotechnic, (9) is a bolt clutch, (10) is a latch, (11) is a latch rotating pin, and (12) is a latch pin. Stoppers. In the drawings, the same reference numerals indicate the same or corresponding parts.
Claims (1)
投入するためのロケツト，および上記衛星に搭載され，
衛星がロケツトによりトランスフアー軌道に投入された
後，静止軌道に移るための作動するアポジ・キツク・エ
ンジンとを結合・分離する方法において，ロケツト側ペ
イロード・アタツチ・フイツテイング，アポジ・キツク
・エンジンおよび衛星とを共通の分離ボルトで結合し，
さらに衛星とアポジ・キツク・エンジンとをラツチ機構
で結合し，上記衛星がロケツトによつてトランスフアー
軌道に投入された後，上記分離ボルトを外してロケツト
およびペイロード・アタツチ・フイツテイングを分離
し，ロケツト分離後，衛星はラツチ機構によりアポジ・
キツク・エンジンと結合状態で，アポジ・キツク・エン
ジンの推力により静止軌道に投入され，しかる後上記ラ
ツチ機構を外し，アポジ・キツク・エンジンを衛星より
分離するようにしたことを特徴とする衛星とロケツトお
よびアポジ・キツク・エンジンとの結合／分離方法。1. A satellite, a rocket for putting the satellite into a transfer orbit, and a rocket mounted on the satellite,
A method for combining and separating an operating apogee kick engine for moving to a geosynchronous orbit after a satellite is introduced into a transfer orbit by a rocket, comprising: a rocket-side payload attack fitting; an apogee kick engine; and a satellite. And with a common separation bolt,
Further, the satellite and the apogee kick engine are connected by a latch mechanism, and after the satellite is put into a transfer orbit by a rocket, the above-mentioned separation bolt is removed to separate the rocket and the payload attachment and the rocket is separated. After separation, the satellite is apogee-
A satellite in which the apogee kick engine is inserted into a geostationary orbit by the thrust of the apogee kick engine in a combined state with the kick engine, and then the latch mechanism is removed to separate the apogee kick engine from the satellite. How to connect / disconnect to rocket and apogee kick engine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1286083A JP2609729B2 (en) | 1989-11-02 | 1989-11-02 | Combination / separation method between satellite and rocket and apogee kick engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1286083A JP2609729B2 (en) | 1989-11-02 | 1989-11-02 | Combination / separation method between satellite and rocket and apogee kick engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH03148400A JPH03148400A (en) | 1991-06-25 |
| JP2609729B2 true JP2609729B2 (en) | 1997-05-14 |
Family
ID=17699722
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP1286083A Expired - Fee Related JP2609729B2 (en) | 1989-11-02 | 1989-11-02 | Combination / separation method between satellite and rocket and apogee kick engine |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP2609729B2 (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| ES2166234B1 (en) | 1998-11-18 | 2003-02-16 | Eads Constr Aeronauticas Sa | A SYSTEM OF MODIFICATION OF THE PROPERTIES OF RIGIDITY / AMORTIGUATION OF STRUCTURAL UNIONS. |
| CN105292523A (en) * | 2015-10-27 | 2016-02-03 | 浙江大学 | Separating device and satellite and rocket separating device with buffering structure |
| CN113280695A (en) * | 2021-06-10 | 2021-08-20 | 北京星途探索科技有限公司 | But single face reassembling type disengaging structure device |
-
1989
- 1989-11-02 JP JP1286083A patent/JP2609729B2/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| JPH03148400A (en) | 1991-06-25 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| LAPS | Cancellation because of no payment of annual fees |