FIELD: automatic control of non-stationary objects, mainly spacecraft. SUBSTANCE: proposed system is used for control of turn of spacecraft to required attitude position. Proposed system includes selector switch and the following units: module determination unit, square root calculation unit, angular velocity minimum signal selection unit, storage unit, preset angular velocity shaping unit and time setting unit. Besides that, system includes minimum acceleration and permissible angular velocity setters, first multiplier, functional amplifier and non-linear element with limitation. Functional amplifier includes fourth amplifier, second multiplier and first and second division units. Preset angular velocity shaping unit has three multipliers, amplifier, second square root determination unit, two comparison elements and third division unit. Control system optimizes transient process by high speed of response under conditions of considerable instability of efficiency of control engines and parameters of spacecraft. They are stipulated by failures of these engines, for example, change of mass of spacecraft at burn-out of fuel in main cruise engine, etc. EFFECT: reduced consumption of fuel at optimal high speed response of turn of spacecraft. 3 cl, 7 dwg
