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.
Gyroless yaw control system for a three axis stabilized, zero-momentum spacecraft
1993-04-27
Miscellaneous
No indication
English
A Gyroless Yaw Attitude Estimator For NOAA-11 - A Zero Momentum Spacecraft (AAS 93-296)
British Library Conference Proceedings | 1993
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British Library Conference Proceedings | 1993
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