| タイトル | Using Fast-Steering Mirror Control to Reduce Instrument Pointing Errors Caused by Spacecraft Jitter |
| 本文（外部サイト） | http://hdl.handle.net/2060/19960042783 |
| 著者（英） | Cuda, Vince; Antol, Jeffery; Holtz, Ted M.; Johnson, Thomas A. |
| 著者所属（英） | Computer Technology Associates, Inc. |
| 発行日 | 1996-06-01 |
| 言語 | eng |
| 内容記述 | The scope of this study was to investigate the benefit of using feedback control of a Fast Steering Mirror (FSM) to reduce instrument pointing errors. Initially, the study identified FSM control technologies and categorized them according to their use, range of applicability, and physical requirements. Candidate payloads were then evaluated according to their relevance in use of fast steering minor control technologies. This leads to the mission and instrument selection which served as the candidate mission for numerical modeling. A standard SmallSat was designed in order to accommodate the payload requirements (weight, size, power, etc.). This included sizing the SmallSat bus, sizing the solar array, choosing appropriate antennas, and identifying an attitude control system (ACS). A feedback control system for the FSM compensation was then designed, and the instrument pointing error and SmallSat jitter environment for open-loop and closed-loop FSM control were evaluated for typical SmallSat disturbances. The results were then compared to determine the effectiveness of the FSM feedback control system. |
| NASA分類 | Spacecraft Design, Testing and Performance |
| レポートNO | 96N31732
NASA-CR-201583
NAS 1.25-201583 |
| 権利 | No Copyright |
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