| タイトル | Gyroless yaw control system for a three axis stabilized, zero-momentum spacecraft |
| 本文（外部サイト） | http://hdl.handle.net/2060/20080004284 |
| 著者（英） | Stetson, Jr., John B. |
| 著者所属（英） | General Electric Co. |
| 発行日 | 1993-04-27 |
| 言語 | eng |
| 内容記述 | A satellite attitude control system is usable in the absence of any inertial yaw attitude reference, such as a gyroscope, and in the absence of a pitch bias momentum. Both the roll-yaw rigid body dynamics and the roll-yaw orbit kinematics are modelled. Pitch and roll attitude control are conventional. The model receives inputs from a roll sensor, and roll and yaw torques from reaction wheel monitors. The model produces estimated yaw which controls the spacecraft yaw attitude. |
| NASA分類 | Spacecraft Design, Testing and Performance |
| 権利 | No Copyright |
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