JPH0452160Y2 - - Google Patents

Info

Publication number
JPH0452160Y2
JPH0452160Y2 JP1985031777U JP3177785U JPH0452160Y2 JP H0452160 Y2 JPH0452160 Y2 JP H0452160Y2 JP 1985031777 U JP1985031777 U JP 1985031777U JP 3177785 U JP3177785 U JP 3177785U JP H0452160 Y2 JPH0452160 Y2 JP H0452160Y2
Authority
JP
Japan
Prior art keywords
yaw
spin
wire
restoring force
rotated
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
Application number
JP1985031777U
Other languages
Japanese (ja)
Other versions
JPS61147700U (en
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed filed Critical
Priority to JP1985031777U priority Critical patent/JPH0452160Y2/ja
Publication of JPS61147700U publication Critical patent/JPS61147700U/ja
Application granted granted Critical
Publication of JPH0452160Y2 publication Critical patent/JPH0452160Y2/ja
Expired legal-status Critical Current

Links

Landscapes

  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)

Description

【考案の詳細な説明】 (産業上の利用分野) 本考案はフリーな物体に受動的な方法により回
転運動を与えるスピンアツプ機構、さらに詳しく
いえば、ロケツトから分離された人工衛星のスピ
ンアツプに好適なヨーを利用したスピンアツプ機
構に関する。
[Detailed description of the invention] (Field of industrial application) The present invention is a spin-up mechanism that imparts rotational motion to a free object by a passive method, and more specifically, a spin-up mechanism suitable for spin-up of an artificial satellite separated from a rocket. Concerning a spin-up mechanism using yaw.

(従来の技術) フリーな物体の一例として地球を周回する人工
衛星が存在する。
(Prior Art) An example of a free object is an artificial satellite orbiting the earth.

従来、人工衛星のスピンアツプを図るものとし
て推進装置による燃料噴射がある。
Conventionally, fuel injection by a propulsion device has been used to increase the spin-up of an artificial satellite.

第4図はこの従来のスピンアツプ機構の一実施
例を示す機構図である。同図において、1は被回
転体(人工衛星)、2はノズル、3は燃料タンク、
4は配管、5は開閉弁である。
FIG. 4 is a mechanical diagram showing one embodiment of this conventional spin-up mechanism. In the figure, 1 is a rotating object (artificial satellite), 2 is a nozzle, 3 is a fuel tank,
4 is a pipe, and 5 is an on-off valve.

開閉弁5を開成し、所定のスピンアツプを得ら
れるようにノズル2a,2bよりそれぞれ反対の
接線方向に燃料噴射を行ない、これにより発生す
るトルクで人工衛星1に回転運動を与えるように
構成されている。
The opening/closing valve 5 is opened, and fuel is injected from the nozzles 2a and 2b in opposite tangential directions to obtain a predetermined spin-up, and the generated torque gives rotational motion to the satellite 1. There is.

(考案が解決しようとする問題点) 従来のスピンアツプ機構はこのように燃料を必
要とし、燃料タンク、ノズル、それらを接続する
配管および開閉弁が付設されるため装置が大掛か
りになる欠点があつた。
(Problems that the invention aims to solve) Conventional spin-up mechanisms require fuel as described above, and have the disadvantage that the device is large-scale because it requires a fuel tank, a nozzle, piping to connect them, and an on-off valve. .

本考案の目的はこれらの欠点を解決するもの
で、直線形状に復元力が作用するワイヤよりなる
ヨーを用いその復元力を利用することによつて、
シンプルな機構で、しかも、特別のエネルギー源
を持つことなく被回転体に回転運動を与えること
ができるスピンアツプ機構を提供することにあ
る。
The purpose of this invention is to solve these drawbacks by using a yaw made of wire that exerts a restoring force on a straight line, and by utilizing that restoring force.
To provide a spin-up mechanism which is a simple mechanism and can give rotational motion to a rotated body without having a special energy source.

(問題点を解決するための手段) 前記目的を達成するために本考案によるスピン
アツプ機構は直線形状に復元力が作用するワイヤ
よりなるヨーを、被回転体に巻き付け、その先端
を係止し、係止を解除してヨーマスを解放したと
き、前記復元力により展開されるヨーの反作用で
前記被回転体に回転運動を与えるように構成され
ている。
(Means for Solving the Problems) In order to achieve the above object, the spin-up mechanism according to the present invention wraps a yaw made of a wire on which a restoring force acts in a linear shape around a rotated body, locks the tip of the yaw, When the yaw mass is released by releasing the lock, the rotational movement is applied to the rotated body by the reaction of the yaw developed by the restoring force.

(作用) 前記構成によれば装置の構成が単純となり、本
考案の目的を完全に達成することができる。
(Function) According to the above structure, the structure of the device becomes simple, and the object of the present invention can be completely achieved.

(実施例) 以下、図面を参照して本考案をさらに詳しく説
明する。
(Example) Hereinafter, the present invention will be explained in more detail with reference to the drawings.

第1図は本考案によるスピンアツプ機構の実施
例を示す図で、フリーな被回転体として人工衛星
に施こした例である。図において、6は人工衛星
の重心9を含む面内に巻き付けられたバネ材を使
用したワイヤ、7はワイヤの先端に取付けられた
ヨーマス、8はヨーを展開するまで保持するため
のロツク機構および展開後ヨーを人工衛星から切
離すためのリリース機構である。
FIG. 1 is a diagram showing an embodiment of the spin-up mechanism according to the present invention, and is an example in which the spin-up mechanism is applied to an artificial satellite as a free rotating body. In the figure, 6 is a wire using a spring material wound in a plane containing the center of gravity 9 of the satellite, 7 is a yaw mass attached to the tip of the wire, 8 is a lock mechanism for holding the yaw until it is deployed, and This is a release mechanism to separate the yaw from the satellite after deployment.

第2図および第3図は第1図の平面図で本機構
の動作過程を示すものである。第1図においてロ
ツク機構8の解除によつてヨーマス7は解放され
ワイヤ6は自体のバネ性の復元力で展開される。
この展開過程で、人工衛星1はヨーからリアクシ
ヨントルクが与えられ回転運動を始める。第2図
はこのときの様子を示したものである。第2図に
示されるように展開中はヨーのワイヤは人工衛星
1に対して接線方向に展開するが、展開完了後、
ヨーの展開方向は回転の半径方向に方向を変え
る。展開方向が半径方向に達した時点でリリース
機構8により人工衛星1からヨーが切離され、ス
ピンアツプが完了する。第3図はそのときの様子
を示すものである。
FIGS. 2 and 3 are plan views of FIG. 1, showing the operating process of this mechanism. In FIG. 1, the yaw mass 7 is released by releasing the lock mechanism 8, and the wire 6 is expanded by its own spring restoring force.
During this deployment process, the artificial satellite 1 is given a reaction torque from yaw and begins to rotate. FIG. 2 shows the situation at this time. As shown in Figure 2, during deployment, the yaw wire deploys tangentially to the satellite 1, but after deployment is complete,
The direction of yaw development changes direction in the radial direction of rotation. When the deployment direction reaches the radial direction, the release mechanism 8 separates the yaw from the artificial satellite 1, completing the spin-up. FIG. 3 shows the situation at that time.

(考案の効果) 以上、説明したように、本考案によればヨーマ
ス、ワイヤ(ヨー)およびロツク・リリース機構
よりなるシンプルなスピンアツプ機構で被回転体
に回転運動を与えることができる。
(Effects of the Invention) As described above, according to the present invention, a rotational motion can be given to a rotated object using a simple spin-up mechanism consisting of a yaw mass, a wire (yaw), and a lock/release mechanism.

また、受動的(ワイヤ自体が保持しているエネ
ルギーを回転運動として被回転体に与えながら、
被回転体より分離させられる意味)に被回転体を
スピンアツプするため、回転に燃料および電力等
のエネルギー源を必要としない利点がある。した
がつてロケツトから分離される人工衛星のスピン
アツプ機構としてシンプルな機構で大掛かりにな
らない点において最適である。
In addition, passive (while applying the energy held by the wire itself to the rotated object as rotational motion,
Since the object to be rotated is spun up (in the sense that it is separated from the object to be rotated), there is an advantage that energy sources such as fuel and electric power are not required for rotation. Therefore, it is ideal as a spin-up mechanism for an artificial satellite that is separated from a rocket because it is a simple mechanism and does not require a large scale.

【図面の簡単な説明】[Brief explanation of the drawing]

第1図は本考案によるスピンアツプ機構の実施
例を示す斜視図、第2図および第3図は本考案に
よるスピンアツプ機構の動作過程をそれぞれ示す
平面図、第4図は従来のスピンアツプ装置の一例
を示す斜視図である。 1……被回転体(人工衛星)、2……ノズル、
3……燃料タンク、4……配管、5……開閉弁、
6……バネ材を使用したワイヤ、7……ヨーマ
ス、8……ロツク・リリース機構、9……被回転
体(人工衛星)の重心。
FIG. 1 is a perspective view showing an embodiment of the spin-up mechanism according to the present invention, FIGS. 2 and 3 are plan views showing the operating process of the spin-up mechanism according to the present invention, and FIG. 4 is an example of a conventional spin-up device. FIG. 1... Rotating object (artificial satellite), 2... Nozzle,
3...Fuel tank, 4...Piping, 5...Opening/closing valve,
6... Wire using spring material, 7... Yaw mass, 8... Lock/release mechanism, 9... Center of gravity of the rotating object (artificial satellite).

Claims (1)

【実用新案登録請求の範囲】[Scope of utility model registration request] 直線形状に復元力が作用するワイヤよりなるヨ
ーを、被回転体に巻き付け、その先端を係止し、
係止を解除してヨーマスを解放したとき、前記復
元力により展開されるヨーの反作用で前記被回転
体に回転運動を与えるように構成したスピンアツ
プ機構。
A yaw made of wire that exerts restoring force in a straight line is wrapped around the rotated object, and its tip is locked.
When the yaw mass is released by releasing the lock, the spin-up mechanism is configured to give rotational motion to the rotated body by the reaction of the yaw developed by the restoring force.
JP1985031777U 1985-03-06 1985-03-06 Expired JPH0452160Y2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP1985031777U JPH0452160Y2 (en) 1985-03-06 1985-03-06

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP1985031777U JPH0452160Y2 (en) 1985-03-06 1985-03-06

Publications (2)

Publication Number Publication Date
JPS61147700U JPS61147700U (en) 1986-09-11
JPH0452160Y2 true JPH0452160Y2 (en) 1992-12-08

Family

ID=30532687

Family Applications (1)

Application Number Title Priority Date Filing Date
JP1985031777U Expired JPH0452160Y2 (en) 1985-03-06 1985-03-06

Country Status (1)

Country Link
JP (1) JPH0452160Y2 (en)

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5856698B2 (en) * 1974-05-09 1983-12-16 レイフ イヨルゲン インゲマ− ルンドブラツド Sheet-shaped object storage device

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5856698U (en) * 1981-10-14 1983-04-16 株式会社日立製作所 Holding and releasing structure for components used after satellite launch

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5856698B2 (en) * 1974-05-09 1983-12-16 レイフ イヨルゲン インゲマ− ルンドブラツド Sheet-shaped object storage device

Also Published As

Publication number Publication date
JPS61147700U (en) 1986-09-11

Similar Documents

Publication Publication Date Title
US9555904B2 (en) Gossamer apparatus and systems for use with spacecraft
JPS52127091A (en) Portable generator
JPH0452160Y2 (en)
JPS5924040B2 (en) Torque generator for controlling artificial satellites, etc.
CN216783904U (en) Satellite derailment release device
JPS6210240Y2 (en)
JPS55140466A (en) Tape applying device
JPS6247760B2 (en)
JPS6137160B2 (en)
JPH0741880B2 (en) Structure deployment method
JPH08119199A (en) Space mount device holding device
JPH04278899A (en) Holding releasing device for development type solar battery paddle
JPH03110000U (en)
Bainum et al. Spacecraft detumbling using movable telescoping appendages
Liu Orientation and resonance locks for satellites in the elliptic orbit
JPS58135400U (en) spin-stabilized satellite
JPH05213289A (en) Clamp cable for expansive structure
HANADA et al. A Feasibility Study of the Tether Assisted Propulsion
JPS54159567A (en) Gyro device
JP2000038981A (en) Motive power device making use of waveforce for generating electricity in such way that let float attached to each lever be moved up and down, let vertical movement be transformed into rotary movement, and let generator be rotated by the rotary movement
JPS62103298A (en) Method of stopping revolution of artificial satellite
JPS61169900U (en)
JPH0624398A (en) Spin imparting device for spacecraft and the like
JPS5544474A (en) Wire unwinding device
JPH0243800U (en)