| Item type |
紀要論文 / Departmental Bulletin Paper(1) |
| 公開日 |
2015-03-26 |
| タイトル |
|
|
タイトル |
第3号科学衛星SRATSの姿勢制御システム(I) |
| 言語 |
|
|
言語 |
jpn |
| 資源タイプ |
|
|
資源タイプ識別子 |
http://purl.org/coar/resource_type/c_6501 |
|
資源タイプ |
departmental bulletin paper |
| その他のタイトル（英） |
|
|
その他のタイトル |
Magnetic Attitude Control System for the No. 3 Scientific Satellite (I) |
| 著者 |
斎藤, 成文
野村, 民也
二宮, 敬虔
長谷川, 幸雄
沢野, 進
原, 躬千夫
SAITO, Shigebumi
NOMURA, Tamiya
NINOMIYA, Keiken
HASEGAWA, Yukio
SAWANO, Susumu
HARA, Michio
|
| 著者所属 |
|
|
|
東京大学宇宙航空研究所 |
| 著者所属 |
|
|
|
東京大学宇宙航空研究所 |
| 著者所属 |
|
|
|
東京大学宇宙航空研究所 |
| 著者所属 |
|
|
|
東京大学宇宙航空研究所 |
| 著者所属 |
|
|
|
日立製作所中央研究所 |
| 著者所属 |
|
|
|
日立製作所中央研究所 |
| 著者所属（英） |
|
|
|
en |
|
|
Institute of Space and Aeronautical Science |
| 著者所属（英） |
|
|
|
en |
|
|
Institute of Space and Aeronautical Science |
| 著者所属（英） |
|
|
|
en |
|
|
Institute of Space and Aeronautical Science |
| 著者所属（英） |
|
|
|
en |
|
|
Institute of Space and Aeronautical Science |
| 出版者 |
|
|
出版者 |
東京大学宇宙航空研究所 |
| 書誌情報 |
東京大学宇宙航空研究所報告
巻 6,
号 2,
p. 416-453,
発行日 1970-04
|
| 抄録（英） |
|
|
内容記述タイプ |
Other |
|
内容記述 |
The No.3 Satellite (SRATS) is a scientific satellite now being developed at the Institute of Space and Aeronautical Science, University of Tokyo. Its function is to obtain measurement data on aeronomy to investigate the relationships between solar radiations and thermospheric structure. The nominal mission requires that the spin axis be oriented normal to the orbital plane at a spin rate of about 10 rpm. It has been expected that a magnetic attitude and spin-rate control system will most advantageously be used to fullfil the requirement. This paper describes the results of the studies on the attitude and spin-rate control system to be used in the No.3 Satellite. Detailed mathematical development of the basic theory and the numerical results are presented. Then, by taking into account various factors influencing the system design, a control system tentatively designed by the authors is described. The satellite borne part of the control system consists of (1) a precession damper, (2) a yo-yo despinner, (3) a spin-axis orientation control device, (4) a spin-rate control device, (5) a spin-axis deviation control device, and (6) attitude and spin-rate detectors. These are linked by telemetry and command to the control computer on the ground. Each of the devices (3), (4), and (5) makes use of the interaction of the internally produced magnetic moment with the earth's magnetic field. The maximum weight and power consumption of the system are expected to be about 5.5 kg and 6 watts respectively. With the aid of a simple computer simulation of the control sequence, it is shown that the desired attitude and spin-rate will be acquired within a week after the injection into orbit and will be kept thereafter. Analyses of possible failure modes and operational compatibility between the subsystems are also included. |
| ISSN |
|
|
収録物識別子タイプ |
ISSN |
|
収録物識別子 |
0563-8100 |
| 書誌レコードID |
|
|
収録物識別子タイプ |
NCID |
|
収録物識別子 |
AN00161914 |
| 資料番号 |
|
|
内容記述タイプ |
Other |
|
内容記述 |
資料番号: SA0125345000 |
SA0125345.pdf (2.2 MB)
