| タイトル | Geostationary Operational Environmental Satellite (GOES) mission profile |
| 著者（英） | Defazio, R. L.; Bryant, W. C.; Sauter, J. A. |
| 著者所属（英） | NASA Goddard Space Flight Center |
| 発行日 | 1986-01-01 |
| 言語 | eng |
| 内容記述 | The GOES mission profile used to achieve geostationary orbit following separation from the Delta launch vehicle is described. The mission profile was constrained by the solid-propellant apogee kick motor which was undersized relative to the spacecraft weight. The resulting deficiency in delivered delta-V had to be made up by the spacecraft hydrazine propulsion system. The mission profile which best utilizes the on-board hydrazine requires that the transfer orbit apogee height be biased 13,800 km above geosynchronous altitude. This maximizes the effectiveness of the apogee motor in performing the plane change necessary to achieve near-equatorial orbit. The highly eccentric drift orbit which results from the apogee motor firing has an average drift rate of 60 deg/day. Circularizing this orbit requires maneuvers designed to achieve geostationary position within a tightly constrained hydrazine allocation. The sequence takes advantage of the orbit changes resulting from attitude maneuvers and combined inplane/out-of-plane maneuvers to achieve hydrazine savings. |
| NASA分類 | ASTRODYNAMICS |
| レポートNO | 87N10123 |
| 権利 | No Copyright |
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