FIELD: space technology. SUBSTANCE: spacecraft attitude control system changes, in a given time, spatial orientation of a spacecraft from initial attitude position to the desired final attitude position. The proposed system determines automatically the angular momentum required to be applied to the spacecraft body to rotate it from initial attitude position to the desired final attitude position, with no controlling momentums for the most part of the rotation. The factored momentum is calculated by loop formed by attitude change parameters update module, attitude miss measuring module, attitude parameters correction module, attitude vector storage module, deceleration thrust impulse direction computation module, memory and attitude change vector commutation block. The control system finds algorithmic solution for the boundary-value problem of determination of angular velocities. EFFECT: decreased fuel consumption for dynamic symmetrical spacecraft attitude change; controllability of dynamic asymmetrical spacecraft attitude change. 4 dwg
