| タイトル | Geostationary Operational Environmental Satellite (GOES) Gyro Temperature Model |
| 本文（外部サイト） | http://hdl.handle.net/2060/19960035763 |
| 著者（英） | Noonan, C. H.; Garrick, J.; Rowe, J. N. |
| 著者所属（英） | NASA Goddard Space Flight Center |
| 発行日 | 1996-05-01 |
| 言語 | eng |
| 内容記述 | The geostationary Operational Environmental Satellite (GOES) 1/M series of spacecraft are geostationary weather satellites that use the latest in weather imaging technology. The inertial reference unit package onboard consists of three gyroscopes measuring angular velocity along each of the spacecraft's body axes. This digital integrating rate assembly (DIRA) is calibrated and used to maintain spacecraft attitude during orbital delta-V maneuvers. During the early orbit support of GOES-8 (April 1994), the gyro drift rate biases exhibited a large dependency on gyro temperature. This complicated the calibration and introduced errors into the attitude during delta-V maneuvers. Following GOES-8, a model of the DIRA temperature and drift rate bias variation was developed for GOES-9 (May 1995). This model was used to project a value of the DIRA bias to use during the orbital delta-V maneuvers based on the bias change observed as the DIRA warmed up during the calibration. The model also optimizes the yaw reorientation necessary to achieve the correct delta-V pointing attitude. As a result, a higher accuracy was achieved on GOES-9 leading to more efficient delta-V maneuvers and a propellant savings. This paper summarizes the: Data observed on GOES-8 and the complications it caused in calibration; DIRA temperature/drift rate model; Application and results of the model on GOES-9 support. |
| NASA分類 | Astrodynamics |
| レポートNO | 96N30502 |
| 権利 | No Copyright |
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