Abstract
In this paper, the mathematical model of a flexible spacecraft system composed of a hub and two symmetrical beams loaded with tip masses is reconsidered to design a control law for internal disturbance rejection. This model has a port-Hamiltonian structure and is passive. The disturbance rejection is performed by a feedback control law using the angular rates at the two tips of a beam. The closed-loop asymptotic stability of such a collocated / non-collocated control is analyzed through explicitly solving the Partial Differential Equations (PDE) of the system. Finally, the experimental results are carried out to assess the validity of the proposed control methodology.
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