Attitude dynamics of a satellite in a low circular orbit is analyzed taking into account the rotating aerodynamic torque resulting due to special installation of solar panels. The existence of the stationary rotations in the orbital reference frame is studied. The number of these rotations is analyzed analytically and numerically. For several specific cases, stability analysis is performed. For the asymptotically stable rotations, the speed of response is estimated.

satellite, aerodynamic torque, autorotation, stationary rotation, stability

Theoretical and applied problems of mechanics