Abstract:This paper mainly focuses on the maneuver of the
satellite in orbit. A non-linear multi-inputs multi-outputs model
has been derived from Newton-Euler equations of motion. The
dynamics is presented with control methodologies allowing the
Extended Kalman Filter (EKF) to iteratively provide improved
data sets with zero errors. As the system is distracted from the
atmospheric swings which are random hence the problem of
stochastic disturbance is furnished. A set of differential equations
of two dimensional Ito sto… Show more
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