| タイトル | Zero-gyro control of the International Ultraviolet Explorer |
| 著者（英） | Hoffman, Henry C.; O'Donnell, James R., Jr. |
| 著者所属（英） | NASA Goddard Space Flight Center |
| 発行日 | 1993-01-01
1993 |
| 言語 | eng |
| 内容記述 | The IUE was built for an anticipated lifespan of three years with a goal of five. It has been operating for over 15 years, even though it has had only two working gyros since August 17, 1985, through the use of a two-gyro attitude control system that uses information from IUE's fine sun sensor (FSS) and the two remaining gyros to provide three-axis control. A one-gyro control system that uses an additional axis of information from the FSS has been developed and tested on-orbit. The purpose of this paper is to discuss the work in progress towards the development of a zero-gyro control law for IUE. Motion about the sunline, which cannot be measured by the FSS, is measured and controlled in the zero-gyro system by applying a momentum bias perpendicular to the sunline and measuring the transfer of this momentum between the spacecraft reaction wheels, while the spacecraft is held in the other two axes using position and derived-rate information from the FSS. |
| NASA分類 | SPACECRAFT DESIGN, TESTING AND PERFORMANCE |
| レポートNO | 93A51355
AIAA PAPER 93-3760 |
| 権利 | Copyright |
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