NONLINEAR ATTITUDE CONTROL OF THE MICRO-SATELLITE ESEO

In this paper, attitude control of a spacecraft using thrusters and reaction wheels as actuators is studied. Linearization and Lyapunov theory is used to derive two linear and four nonlinear controllers. Three of the nonlinear controllers rely on cancellation of system nonlinearities, while the fourth is a sliding mode controller. By restricting the spacecraft inertia, simpler controllers can be found. Several controllers are compared in simulations. The simulations are based on data from the micro-satellite, European Student Earth Orbiter (ESEO).

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