Optimal Control of Low Propulsion Orbital Transfer Time

Within operational life of satellites according to their mission, need to change their operational orbits. This change can includes change in semi-major axis, inclination or plane of orbit (RAAN angle). For this propose, we can use Electrical Propulsion (EP). With respect to light weight of EP in cases which there is weight constraint, we use EP for transfer satellite to desired orbit. In this paper, we consider minimum-time transfer problem for these transfers. Initial and final orbits are circular and we assume thrust is continuous. Assuming constant acceleration, elements of orbit uniformly change and these changes analyze with Edelbaum Analysis.