Several schemes in current use for sequential estimation of spacecraft attitude using Kalman filters are examined. These differ according to their treatment of the attitude error, namely: using the complete four-component quaternion; using a truncated quaternion in which one of the components has been eliminated; or using a quaternion referred to approximate body-fixed axes. These schemes are examined for the case of a spacecraft carrying line-of-sight attitude sensors and three-axis gyros whose measurements are corrupted by noise on both the drift rate and the drift-rate ramp. The analysis of the covariance is carried out in detail. The historical development of Kalman filtering of attitude is reviewed.
Kalman filtering for spacecraft attitude estimation
Aerospace Sciences Meeting ; 1982 ; Orlando, FL
1982-01-01
Conference paper
No indication
English
Kalman filtering for spacecraft attitude estimation
AIAA | 1982
|Kalman Filtering for Spacecraft Attitude Estimation
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|Quaternion Invariant Extended Kalman Filtering for Spacecraft Attitude Estimation
Online Contents | 2017
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