Low-Thrust Many-Revolutions maneuver optimization for future active debris removal applications

In the last sixty years, space activity has increased exponentially. Satellites in orbit are used for countless purposes and they represent a unique resource for collecting scientific data and for creating new commercial opportunities and various essential applications and services. However, as a consequence of this progressive growth , a new hazard has become a concrete reality: space debris. The great presence of space debris around Earth, and its continuous rise in number and mass, represents a big deal for active and future space missions, due to possible fatal collision, to the point that the majority of space agencies are busily dealing with the problem. In order to understand the relevance of this issue, it’s enough to think that near Earth orbit is so polluted with "space junk" that the International Space Station is continuously moved to avoid impact with dangerous chunks of space debris. The solution is represented by active debris removal mission The purpose of the present study regards the utilization of an indirect method to achieve an optimization of low-thrust many revolutions maneuver for future active debris removal applications. Since multiple target missions would have a greater impact on space debris reduction, a minimal fuel consumption must be achieved, even accepting greater mission times. Electric propulsion is a suitable technology to achieve a low-consumption mission.