Abstract
The manoeuvre of a small satellite in a defined orbit at an accurate position with payload complexity and mass constraint is very challenging. Small satellites are highly prone to circumferential disturbances in space. Mathematical modelling of satellite dynamics is studied in detail. Stability regions are analysed with phase portrait. Feedback linearisation implemented with Uncertainty and Disturbance Estimation (UDE) based controller-observer is designed. The novelty of the research is to robustify the satellite by estimating the overall uncertainties and disturbances. The resultant controller requires the angular positions and angular rates of the spacecraft. The observer provides the angular rate. The closed-loop stability of the overall system has been established. The efficacy of the proposed design is demonstrated on a three-axis nanosatellite. Comparison of proposed strategy is made with other control methods through simulation in Matlab platform.
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