In recent years, space exploration has experienced an exponential increase in activities within low Earth orbit (LEO), a trend that is expected to continue in the coming years. This growth has drawn attention to the problem of orbital debris overcrowding and the need to design missions capable of actively mitigating this issue. As a result, there is a growing interest in developing more efficient missions, particularly in optimizing transfer manoeuvres to minimize either time or propellant consumption. LEO is an environment where the Keplerian orbit approximation alone is insufficient to accurately describe all relevant dynamics. In particular, the perturbation due to Earth’s J2 effect must be considered to obtain precise results.