This paper studies single-axis equations of motion that are applicable to a spacecraft or to a space experiment pointing assembly whose motion has been perfectly isolated from the carrier vehicle. It considers four state estimators for implementation in the control loop for a stellar observation experiment. It is shown via closed-loop covariance analysis that the best achievable pointing performance with the best of the first three estimators is limited to about 0.125 are-sec (rms) with the given rate-gyro and star-tracker inaccuracies. It is also shown that the fourth estimator has the capability of achieving a pointing performance far superior to the performance achievable using the first three estimators. The fourth estimator relies on the ability to accurately generate the desired control torque.
On attitude estimation schemes for fine-pointing control
Lageschaetzungsmethode zur Feinausrichtungssteuerung
IEEE Transactions on Aerospace and Electronic Systems ; 14 , 2 ; 258-265
1978
8 Seiten, 3 Bilder, 8 Tabellen, 8 Quellen
Aufsatz (Zeitschrift)
Englisch
On Attitude Estimation Schemes for Fine-Pointing Control
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