Application of relative orbital elements theory for maneuver reconfiguration in rendezvous operations

This thesis explores the application of Relative Orbital Elements (ROE) theory for impulsive maneuver reconfiguration in rendezvous operations in a generic In-Orbit Servicing (IOS) mission. The objective is to optimize the trajectories of a satellite named Servicer, during the approach phase to a secondary satellite called Target, ensuring safety, fuel efficiency, and compliance with ground station visibility constraints. Various maneuver planning strategies are analyzed, with a particular focus on propellant consumption minimization and the impact of solar activity. The results demonstrate the effectiveness of the ROE-based approach in improving maneuver accuracy and overall mission safety.