Evolution of the Rotational Movement of a Three-Axis Satellite with Ball Damper in Circular Orbit

Abstract

For a triaxial satellite with a spherical damper, the equations of rotational motion in an elliptical orbit in the Biletskii–Chernousko variables are derived. On their basis, for the case of a circular orbit, averaged equations of the second approximation over a small parameter were constructed, describing the evolution of non-resonant rotations of the satellite. Bifurcation curves in the space of phase variables of the system are investigated, at the intersection of which the nature of the rotational motion of the satellite changes significantly.