FIELD: cosmonautics.
SUBSTANCE: invention relates to the field of control of the relative motion of spacecraft (SC) with solar (SB) and rechargeable batteries (RB). By means of solar panels, a positive energy balance of the power supply is provided. Spacecraft is oriented in preset orbit using strapdown inertial unit with unit of star sensors. By means of actuators in the form of gyrodines and electromagnetic control system (EMCS) control moments of action on the spacecraft body are generated. Together with EMCS, jet engines unit is used with low consumption of working medium in modes of damping and stabilization of spacecraft at randomly varying torque created by EMCS. Gyrodynes rotors are smoothly spinned up and RB charging capacity is increased to optimum power supply of the spacecraft and its long-term standard mode.
EFFECT: high efficiency and reliability of spacecraft control while ensuring its long-term high-precision orientation.
1 cl, 2 dwg
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