Attitude control for pitch bias momentum spacecraft at inclind orbit is dicussed in this study. A specific spacecraft model is used in order to provide a practical operational strategy for the attitude maneuver at inclined orbit. Specific types of actuators are assumed and the control strategy is developed based upon those actuators. On-board momentum wheel attached to a pivot and skewed magnetic torquer are employed as primary actuation devices. Real-time ground based attitude estimator is also designed providing yaw angle information using roll angle telemetry data. Simulataneous pitch, and roll/yaw pointing are shown to be possible within certain inclination angle by the proposed method in this research.
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