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CONTROL OVER SPACECRAFT CENTER OF MASS MOVEMENT DURING SOFT RENDEZVOUS WITH ORBITAL OBJECT AT THE SHORT-RANGE GUIDANCE SEGMENT

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A method of spacecraft center of mass motion control using information on line of sight of the passive orbital object to be approached is considered. The structure and value of the coefficient of quasi-optimal fast control law is determined. The coefficient value is adjusted with the account for the spacecraft angular dynamics and acting disturbances, and the distance to the object appropriate for transition from long-range to short-range guidance is defined.

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