| タイトル | The Integration, Testing and Flight of the EO-1 GPS |
| 本文（外部サイト） | http://hdl.handle.net/2060/20010084990 |
| 著者（英） | Shulman, Seth E.; Quinn, David A.; Sager, Jennifer A.; Sanneman, Paul A. |
| 著者所属（英） | NASA Goddard Space Flight Center |
| 発行日 | 2001-06-01 |
| 言語 | eng |
| 内容記述 | The Global Positioning System has long been hailed as the wave of the future for autonomous on-board navigation of low Earth orbiting spacecraft despite the fact that relatively few spacecraft have actually employed it for this purpose. While several missions operated out of the Goddard Space Flight Center have flown GPS receivers on board, the New Millenium Program (NMP) Earth Orbiting-1 (EO-1) spacecraft is the first to employ GPS for active, autonomous on-board navigation. Since EO-1 was designed to employ GPS as its primary source of the navigation ephemeris, special care had to be taken during the integration phase of spacecraft construction to assure proper performance. This paper is a discussion of that process: a brief overview of how the GPS works, how it fits into the design of the EO-1 Attitude Control System (ACS), the steps taken to integrate the system into the EO-1 spacecraft, the ultimate on-orbit performance during launch and early operations of the EO-1 mission and the performance of the on-board GPS ephemeris versus the ground based ephemeris. Conclusions will include a discussion of the lessons learned. |
| NASA分類 | Aircraft Communications and Navigation |
| 権利 | No Copyright |
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