FIELD: space vehicle attitude control systems operated by jet servo elements and powered gyroscopes. SUBSTANCE: method consists in determination of required magnitude of vector of moment of momentum in powered gyroscope system at moment of completing the turn to use this system for dampening residual velocity with no consumption of propellant. To this end, two dynamic modes are combined: maintenance of angular velocity at three-dimensional motion of space vehicle and unloading powered gyroscope to preset level. EFFECT: reduced consumption of working medium required for dampening residual angular velocity at completion of turn of space vehicle due to use of margin of moment of momentum of powered gyroscope system. 6 dwg
