Summary: The problem of minimum-time orbit transfer using intermediate acceleration is analyzed using both precise integration and averaging. Continuous constant accelerations of the order of \(10^{-2}g\) are considered for applications using nuclear propulsion upper stages. The acceleration vector is optimized in direction with its magnitude held constant throughout the flight. These trajectories that circle the Earth for only a few orbits before reaching geostationary Earth orbit are shown to be sensitive to departure and arrival points, necessitating the use of the full six-state dynamics for satisfactory and meaningful results. The \(\Delta V\) losses with respect to very low-acceleration transfers are shown to be small.