Dynamics of a satellite moving in central Newtonian force field in a circular orbit under action of the gravitational and aerodynamic torques is investigated. In the particular case when the center of pressure of aerodynamic forces is located on one of the satellite’s principal central planes of inertia, all equilibrium orientations are determined. Conditions of equilibriums existence are obtained depending on three dimensionless parameters of the system. Detailed investigation of existence domains of various numbers of solutions is carried out. All bifurcational values of parameters at which there is a change of quantity of equilibrium orientations are determined. For each equilibrium orientation sufficient conditions of stability are obtained as a result of the generalized energy integral analysis. Evolution of domains of validity for the stability conditions are studied depending on parameters of the system.

satellite, aerodynamic torque, equilibria, sufficient conditions of stability, bifurcational points

Theoretical and applied problems of mechanics