| タイトル | MAP Attitude Control System Design and Analysis |
| 著者（英） | ODonnell, J. R., Jr.; Campbell, C. E.; Andrews, S. F.; Ericsson-Jackson, A. J.; Markley, F. L. |
| 著者所属（英） | NASA Goddard Space Flight Center |
| 発行日 | 1997-05-01 |
| 言語 | eng |
| 内容記述 | The Microwave Anisotropy Probe (MAP) is a follow-on to the Differential Microwave Radiometer (DMR) instrument on the Cosmic Background Explorer (COBE) spacecraft. The MAP spacecraft will perform its mission in a Lissajous orbit around the Earth-Sun L(sub 2) Lagrange point to suppress potential instrument disturbances. To make a full-sky map of cosmic microwave background fluctuations, a combination fast spin and slow precession motion will be used. MAP requires a propulsion system to reach L(sub 2), to unload system momentum, and to perform stationkeeping maneuvers once at L(sub 2). A minimum hardware, power and thermal safe control mode must also be provided. Sufficient attitude knowledge must be provided to yield instrument pointing to a standard deviation of 1.8 arc-minutes. The short development time and tight budgets require a new way of designing, simulating, and analyzing the Attitude Control System (ACS). This paper presents the design and analysis of the control system to meet these requirements. |
| NASA分類 | Spacecraft Design, Testing and Performance |
| レポートNO | 97N19587 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/541794 |
|
