Dynamics model of a satellite with two solar panels is derived. It is assumed that solar panels are connected to central rigid body by two torsional flexible rods. A model reference adaptive controller is designed and its stability is proven by Lyapunov method. Capability of controller in an attitude maneuver by a numerical simulation is shown.
Adaptive attitude control of a flexible satellite
2006-01-01
1709881 byte
Aufsatz (Konferenz)
Elektronische Ressource
Englisch
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