Parametric Analysis of Active Debris Removal Service for Large LEO Constellations

Low Earth Orbit (LEO) has become a crowded environment due to the increasing number of operational satellites and space debris generated by human activities in space. This overpopulation presents several significant challenges to the sustainability and safety of space activities, requiring careful management and proper disposal of obsolete satellites and orbital debris. Indeed, once their operational life is over, these satellites contribute to the space debris problem, adding to congestion and increasing the risk of collisions with other operational satellites. Therefore, it is critical to adopt effective disposal policies and practices to minimize risks and preserve the sustainability of future space activities. In this context, the European Space Agency (ESA) has developed specific guidelines and regulations that require satellites that are no longer operational to be deorbited in a controlled and safe manner, ensuring they re-enter the Earth's atmosphere and disintegrate completely. This work aims to design an affordable and compatible Active Debris Removal (ADR) service for mega-constellations satellites in LEO orbit, with OneWeb being considered one of the main case studies. This work was conducted in collaboration with D-Orbit, a space company founded in 2011 and a market leader in space logistics and transportation. This thesis first explains the data and modeling assumptions used to define a parametric analysis in the context of an active debris removal mission aimed at servicing one or more satellites of a given constellation. A tool was created for this purpose using MATLAB software, allowing for the variation of all parameters present in a Monte Carlo analysis and obtaining all possible solutions of the ADR service based on the input variables, objectives, and constraints imposed. The objective of the analysis is to determine the most convenient mission architecture considering different distributions of failed satellites. It is important to specify that the following work is based on a previously developed model with relatively simple if reasonable assumptions, seeking to deepen some aspects, particularly that related to the modeling of electric propulsion, in such a way as to obtain results that are more realistic and in accordance with the previously described objective. Finally, lessons learned and opportunities for improvement for future missions are presented.