PROCEDE DE REDUCTION DU MOMENT CINETIQUE ET DE CONTROLE D'ATTITUDE D'UN ENGIN SPATIAL

The method involves aligning the angular momentum of a spacecraft i.e. earth-orbiting satellite along a Z-axis, by slaving the angular momentum, along an X-axis and a Y-axis, respectively, of an angular momentum accumulating device, to the angular velocity of the earth-orbiting satellite, along the Y-axis and the X-axis, respectively. Gyroscopic torques are created to reduce the angular velocities of the earth-orbiting satellite along the X and Y axes, and the angular momentum of the earth-orbiting satellite is reduced by a Z-axis torque generated by a propulsion device of the satellite.