Determination of the conditions for the safe approach of an inspector satellite with a spacecraft in Earth orbit

The article is devoted to the study of the movement of the inspector satellite in the vicinity of the observed spacecraft. The inspector satellite is developed in order to monitor the spacecraft, carry out timely maintenance in order to eliminate malfunctions for its further functioning, refueling, towing, etc. One of the most important stages of the satellite is the approach to the spacecraft, which is planned by modeling using the equations of relative orbital motion, which generation is presented in this article. The rendezvous procedure is carried out by two-pulse maneuver. The article also describes conducted numerical experiments modeling the approach under di erent initial conditions, in which conditions for collision and safe approach of the satellite with the spacecraft, the most convenient observation positions near the spacecraft and the time when it can be observed are determined.