Abstract
The dynamics of a spacecraft with variable mass distribution is considered, assuming a central Newtonian gravitational field. The equations of spatial attitude motion are derived within the framework of the so-called satellite approximation and examined via a Hamiltonian approach. The centre of mass of the satellite multibody system moves along an elliptic orbit of arbitrary eccentricity. For a prescribed attitude motion, control via the mass redistribution is determined. Various classes of relative equilibria are detected, and the respective control is obtained. The stability of the spacecraft spatial attitude motions is examined in detail.
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