Disturbance torque compensated three axis yaw control system
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United States of America Patent
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May 3, 1994
Grant Date -
N/A
app pub date -
Jul 20, 1992
filing date -
Jul 20, 1992
priority date (Note) -
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status (Latency Note)
Importance
Abstract
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. The model further produces estimates of the constant component of the disturbance torques for compensation thereof.
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