Investigation of equilibria of the satellite subjected to action of the gravitational and aerodynamic moments

The dynamics of the setellite moving in a central Newtonian force field in a circular orbit under action of the gravitational and aerodynamic moments is investigated. In specific case, when the center of pressure of aerodynamic forces is located on one of the principal central axes of inertia of the satellite, all equilibrium orientations are determined. Necessary and sufficient conditions of stability are obtained for each equilibrium orientation. Evolution of domains where stability conditions take place is investigated in detail depending on parameters of a problem. All bifurcational values of parameters corresponding to qualitative change of domains of stability are determined .