SPACECRAFT ATTITUDE DETERMINATION USING ELECTROSTATICALLY SUSPENDED GYROS

摘要

The peculiarities of the attitude determination in the ESG-based spacecraft attitude reference system are examined. The gyro drift and the rotor readout system errors are analyzed to make a decision either deterministic or statistical algorithm is preferable in the case of three orthogonally pointed gyros that is under consideration. Additionally, the potentiality of using the informational redundancy for the gyro drift in-flight calibration is demonstrated.