In this paper we present results of an analysis on the dynamics of collision between operational vehicles and space debris on a mission in the regions LEO, MEO and GEO. The maneuvers are ideal because in the first instance, we do not consider the existing dissipative forces in these regions. The analysis established technological parameters of the propulsion system of the vehicle that enables the implementation of evasive maneuvers to debris of different sizes (from millimeters to kilometer), speed (0.5 to 20.0 km/s) and positions (3 to 300 km) initials. Furthermore, we assume that these collisional objects are separated by a small distance relative to the distance from the vehicle to earth. The results showed the possibility of collision from a distribution of the initial conditions, including the angles in-plain and out-plain. A policy of compromise between technological parameters and evasive maneuvers of the collisional debris varying size was established, verifying the existence of technological parameters minimum and characteristic for the orbital regions, in favor of schemes to avoid debris from millimeter sizes.