Optimal Low-Earth-Orbit-Geostationary-Earth-Orbit Intermediate Acceleration Orbit Transfer

The problem of minimum-time orbit transfer using intermediate acceleration is analyzed using both precision integrationand averaging. Continuousconstantaccelerationsoftheorderof10 i 2 gareconsideredforapplications using nuclear propulsion upper stages. The acceleration vector is optimized in direction with its magnitude held constant throughout the e ight. 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 D V losses with respect to very low-acceleration transfers are shown to be small.