JPS6027000U

JPS6027000U - Connection mechanism of rocket motor to artificial satellite

Info

Publication number: JPS6027000U
Application number: JP11990183U
Authority: JP
Inventors: 修平山下
Original assignee: 三菱電機株式会社
Priority date: 1983-08-01
Filing date: 1983-08-01
Publication date: 1985-02-23

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

[Brief explanation of the drawing]

第１図、第２図及び第３図は従来のロケットモータの人
工衛星への連結機構を示す構成図で、第１図は全体構成
図、第２図は第１図に示すＡ−Ａ断面図、第３図は第１
図に示すＢ部詳細図、第４図及び第５図はこの考案のロ
ケットモータの人工衛星への連結機構を示す構成図で、
第４図は全体構成図、第５図は第４図に示すＣ部詳細図
であ乏。図において、１は人工衛星、２はロケットモータ、３は
上部構造体、４はフランジ、５は下部構造体、６はフラ
ンジ、７は■型クランプ、８は爆破ボルト、９は引張型
バネ、１０は支持アーム、１１は圧縮型バネ、１２は内
側フランジ、１３は内側支持アーム、１４は主フレーム
、１５は保持フレーム、１５ａは脚、１５ｂは取付穴、
１６は固定面、１７は取付穴、１８はテーパピン、１９
は分離ボルト、２０ａは固定ボルト、２０ｂはカートリ
ッジナツト、２１はボルトキャッチャ、２２はｉ型バネ
、２３は支持アーム、２４はコネクタ、２５ａは第１の
接栓、２５ｂは第２の接　　　−栓、２６．２７は信号
線である。なお、図中同一あるいは相当部分には同一符
号を付して示しである。Figures 1, 2, and 3 are configuration diagrams showing a conventional coupling mechanism of a rocket motor to an artificial satellite. Figure 1 is an overall configuration diagram, and Figure 2 is a cross section taken along line A-A shown in Figure 1. Figure 3 is the first
The detailed view of part B, Figures 4 and 5 shown in the figure are configuration diagrams showing the mechanism for connecting the rocket motor to the artificial satellite of this invention.
FIG. 4 is an overall configuration diagram, and FIG. 5 is a detailed diagram of section C shown in FIG. 4. In the figure, 1 is an artificial satellite, 2 is a rocket motor, 3 is an upper structure, 4 is a flange, 5 is a lower structure, 6 is a flange, 7 is a ■-type clamp, 8 is an explosive bolt, 9 is a tension type spring, 10 is a support arm, 11 is a compression type spring, 12 is an inner flange, 13 is an inner support arm, 14 is a main frame, 15 is a holding frame, 15a is a leg, 15b is a mounting hole,
16 is a fixed surface, 17 is a mounting hole, 18 is a taper pin, 19
20a is a separation bolt, 20a is a fixing bolt, 20b is a cartridge nut, 21 is a bolt catcher, 22 is an I-type spring, 23 is a support arm, 24 is a connector, 25a is a first plug, and 25b is a second plug. , 26 and 27 are signal lines. Note that the same or equivalent parts in the figures are indicated by the same reference numerals.

Claims

[Scope of utility model registration request]

A connection mechanism for connecting a rocket motor to an artificial satellite includes a holding frame that fixes and holds the outer peripheral surface of the rocket motor and has at least three legs arranged in parallel in the same direction as the axis of the rocket motor; A main frame having a fixing surface provided at a portion where the plurality of legs of the holding frame come into contact with each other; a function of connecting and tightening and fixing the holding frame to the fixing surface of the main frame; A fixing/releasing mechanism consisting of a separation bolt and a cartridge nut filled with gunpowder, which have the function of releasing the tightening/fixing; one end is fixed to the holding frame, and the other end is in contact with the main frame; A separation mechanism equipped with a compression type spring that has a function of separating the holding frame from the satellite by its combined force when the release mechanism releases the fastening fixation between the satellite and the holding frame;
It consists of a first connector attached to the main frame, and a second connector that is attached to the other end of the signal line, one end of which is connected to the rocket motor side, and that engages with the first connector. A mechanism for connecting a rocket motor to an artificial satellite, characterized in that all of these components are arranged in parallel in the same direction with respect to the axis direction of the artificial satellite.