The ever-increasing density of objects in low Earth orbit (LEO) has raised concerns about the potential for a future cascade of collisions, a phenomenon known as the Kessler Syndrome. Such collisions could inflate the amount of space debris, posing significant risks to operational satellites and future space missions. In response to this, and in alignment with new de-orbit regulations, there is a shift towards refining collision avoidance strategies to minimize propellant consumption. Indeed, despite the relatively low fuel requirements of individual collision avoidance maneuvers, their growing necessity places a considerable strain on satellite fuel budgets. In this context, the objective of this research is to develop a tool that uses indirect optimization to identify propellant-efficient collision avoidance trajectories between two orbiting objects.