| タイトル | Navigation Accuracy Guidelines for Orbital Formation Flying Missions |
| 本文（外部サイト） | http://hdl.handle.net/2060/20030102177 |
| 著者（英） | Alfriend, Kyle T.; Carpenter, J. Russell |
| 著者所属（英） | NASA Goddard Space Flight Center |
| 発行日 | 2003-01-01 |
| 言語 | eng |
| 内容記述 | Some simple guidelines based on the accuracy in determining a satellite formation's semi-major axis differences are useful in making preliminary assessments of the navigation accuracy needed to support such missions. These guidelines are valid for any elliptical orbit, regardless of eccentricity. Although maneuvers required for formation establishment, reconfiguration, and station-keeping require accurate prediction of the state estimate to the maneuver we, and hence are directly affected by errors in all the orbital elements, experience has shown that determination of orbit plane orientation and orbit shape to acceptable levels is less challenging than the determination of orbital period or semi-major axis. Furthermore, any differences among the member s semi-major axes are undesirable for a satellite formation, since it will lead to differential along-track drift due to period differences. Since inevitable navigation errors prevent these differences from ever being zero, one may use the guidelines this paper presents to determine how much drift will result from a given relative navigation accuracy, or conversely what navigation accuracy is required to limit drift to a given rate. Since the guidelines do not account for non-two-body perturbations, they may be viewed as useful preliminary design tools, rather than as the basis for mission navigation requirements, which should be based on detailed analysis of the mission configuration, including all relevant sources of uncertainty. |
| NASA分類 | Spacecraft Design, Testing and Performance |
| 権利 | No Copyright |
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