Abstract
Abstract: The colony of a celestial universe has become foremost task for many countries in the late decades. The spinning attitude control for economical satellite operation is widely used. This paper shows a successful implementation of state space technique to inherently unstable satellite spun around longitudinal axis. Full-state feedback and reference input with full-state feedback are compared for deadbeat response. The state space control gains are tuned to satisfy controllability conditions. Observability conditions are checked for better tracking of attitude spinning angle to step input with the aim to achieve a robust spin stabilization of the satellite manoeuvre. Satisfactory deadbeat specifications are obtained based on reference input with full-state feedback. However, full-state feedback implements reasonable design gains and it appears to be slower in judgment with reference input with full-state feedback gains. The simulation and analytical results are well agreed based on dominant second-order poles.
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