FIELD: space technology. SUBSTANCE: method involves application of damping effort to spacecraft body along channels of rolling and/or yawing motion for damping oscillating angular motion, orientation of cross section of flexible removable member having anisotropic rigidly in parallel with vector of bending moment originating during oscillating angular motion of spacecraft round axis of pitching motion, measuring and memorizing of angles between adjacent main central axes of inertia of cross section of flexible removable member, and between main central axes and vector of bending moment and turn of flexible removable member round axis perpendicular to its cross section until achievement of angles between axis of inertia of cross section and axis of spacecraft aligning with vector of bending moment, calculated value being more than zero but smaller than memorized angle between adjacent main central axes of inertia of cross section. During maintenance of orbital orientation of spacecraft turn of flexible removable members mounted symmetrically to center of masses of spacecraft is carried out in the same side and to the same angle round axis directed from center of masses of spacecraft to point of fastening of removable member on the spacecraft body. During keeping orientation with application of linear control effort to the spacecraft body, for example, during correction of orbit turn of flexible removable members mounted in symmetry with center of masses of the spacecraft is carried out in opposite sides to the same angle round axis directed from center of masses of the spacecraft to point of fastening of removable member on the spacecraft body connected to flexible removable members of coordinate system. EFFECT: enhanced stabilization reliability. 3 cl, 4 dwg
