The attitude estimation of a rigid spacecraft from the noise-corrupted measures provided by sensors is studied. The method used is based on the EKF algorithm and, due to the lack of precision that can exist on the values of certain parameters, an augmented state-vector comprising these parameters must be considered. The filter then provides an estimation of these parameters along with the original state-variables of the system. The method is implemented using simulated model.
State-estimation and parameter identification of freely-spinning rigid spacecraft
Zustandsabschaetzung und Parameteridentifizierung von starren Raumfahrzeugen mit freier Spinbewegung
International Journal of Systems Science ; 7 , 12 ; 1377-1386
1976
10 Seiten, 4 Quellen
Article (Journal)
English
Kalman Filter for Spinning Spacecraft Attitude Estimation
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