A reformulation of Edelbaum's equations for low thrust orbit raising between two circular orbits with an inclination change using optimal control theory was performed. A nonsingular modified equinoctial element set was used, and higher order gravitational harmonics up to and including J5 were included within the model. An indirect optimization scheme was performed to optain an optimal pitch steering law, and the state and costate equations were solved using a Legendre-Gauss-Radau collocation scheme. The numerical solution was broken up into two phases. The first phase has the objective of raising an orbit into a zone in which eclipsing is no longer an issue, and the second phase involves solving a two-point boundary value problem in order to finish the maneuver.