FIELD: space engineering. SUBSTANCE: proposed method includes plotting and maintaining preset orientation of spacecraft, measuring spacecraft motion parameters and determining position of center of mass by measured parameters. Orientation of spacecraft is maintained by means of powered gyroscopes; jet engines are used for creating disturbing moment having projections other than zero on body axis of spacecraft coordinate system; then, moment of momentum of powered gyroscope, angular velocity of spacecraft and vector of state are measured and inertial characteristics of spacecraft are determined. Proposed method makes it possible to determine position of center of mass and inertia tensor at control of spacecraft by means of powered gyroscope and jet engine creating non-balanced disturbing moments relative to axes of coordinate system rigidly connected with spacecraft. EFFECT: enhanced efficiency and reliability. 3 dwg, 4 tbl
