The paper considers a tow truck recovery spacecraft designed for active removal of a group of the large space debris from a geostationary orbit to the disposal orbit. It finds simplified analytical relationships to compute the spacecraft main subsystems mass depending on the type of a propulsion system used. The paper shows that a tow truck spacecraft equipped with an electric jet propulsion system satisfying existing limitations to the available launch vehicles would be able to perform a mission of removing thirty spent upper stages from a geostationary orbit to the disposal orbit. The paper also demonstrates that when using a sustainer propulsion system equipped with the liquid rocket engine on the long-storable propellant components at a significantly lower development cost, the tow truck spacecraft is able to perform a mission of removing half of the existing space debris. On the one hand, using two spacecraft increases the launch costs; but on the other hand, it allows creating a simpler, more reliable and economical spacecraft, as well as accelerating the geostationary orbit cleaning in case two spacecraft are operating in parallel. Further research should be aimed at analyzing the technical and economic indicators of the two options considered in the work.

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