We investigate the gravity gradient stabilization mode of the Earth artificial satellite designed for microgravity studies. The satellite dimensions and inertia tensor are similar to the same characteristics of the spacecraft Foton and Progress. We consider two variants of the mode - the passive (uncontrollable) variant and the active (controllable) one. Electric propulsions are used for control of satellite attitude motion in the active variant. We check two conditions for both variants: the low level of residual accelerations on board the satellite and the stability of the motion (preservation of its basic properties over a long period of time, insensibility to errors in initial conditions). Checking is caring out by mathematical modeling of the satellite attitude motion. We demonstrate that the active variant provides the low level of accelerations but is not stable relative to errors in initial conditions of the motion. The active variant satisfies two conditions above. Interchange of these variants proves to be more economical: the electric propulsions operate only a few hours every 3 - 5 days to damp arising disturbed motion.

Theoretical and applied problems of mechanics