Aas 08-298 Optimizing Periapsis-raise Maneuvers Using Low-thrust Propulsion

This study considers the optimal control problem of maximizing the raise in the periapsis of a spacecraft orbit using continuous variable low-thrust propulsion. The dynamics of the spacecraft in the two-body system are modeled using Lagrange’s planetary equations with the classic orbit elements as the state variables. Control is provided via the propulsion thrust components in the radial and circumferential directions. In addition, interior and terminal state constraints are considered to maintain the orbit apoapsis at a fixed altitude.