In this paper we present the results of a study of collision dynamics between space debris andoperational vehicles. We adopted an approach based on the relative dynamics between theobjects on a collisional course with short warning time and established a semi-analytical solutionfor the final trajectories of these objects. The results showed that there are angular ranges in 2Dand 3D, in addition to the initial conditions, that favor the collisions. These results allowed theinvestigation of a range of technological parameters of the spacecraft (e.g, fuel reserve) thatallow a safe evasive maneuver (e.g, time available for the maneuver). The numerical model wastested for many different values of the impact velocity and relative distance between theapproaching objects.
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