The report сonsiders the problems of space flight mechanics in relation to promising projects for cleaning near-Earth space from large space debris. It is assumed that one active spacecraft can transfer several such objects into disposal orbits. It is shown that a noticeable increase in mission efficiency can be achieved as a result of three-level optimization. First of all, it is necessary to choose one of two removal variants (using detachable propulsion modules or towing by the spacecraft). Next, transfer schemes are developed, which take into account and use natural gravitational perturbations of the orbit. At the lower level, a maneuvering strategy is selected when flying between the next pair of objects in the transfer chain.

In this research, the approximate altitude boundary of the preferred removal variant is obtained, it depends on six parameters of the mission. The conducted studies for low orbits and the vicinity of the geostationary orbit allowed to put forward requirements for the capabilities of an active spacecraft. For Medium Earth orbits, a detailed review of proposals for choosing a stable or degrading disposal orbit has been performed, taking into account luni-solar resonances.)