State-estimation and parameter identification of freely-spinning rigid spacecraft

This paper studies the attitude estimation of a rigid spacecraft from the noise-corrupted measures provided by sensors. The method used is based on the EKF algorithm and, duo 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 thon provides an estimation of these parameters along with the original state-variables of the system. The method is implemented using a simulated model.