OPTIMAL LOW-EARTH-ORBIT-GEOSTATIONARY-EARTH-ORBIT INTERMEDIATE ACCELERATION ORBIT TRANSFER

The problem of minimum-time orbit transfer using intermediate accelera tion is analyzed using both precision integration and averaging. Conti nuous constant accelerations of the order of 10(-2) g are considered f or applications using nuclear propulsion upper stages. The acceleratio n vector is optimized in direction with its magnitude held constant th roughout the flight. These trajectories that circle the Earth for only a few orbits before reaching geostationary Earth orbit are shown to b e sensitive to departure and arrival points, necessitating the use of the full six-state dynamics for satisfactory and meaningful results. T he Delta V losses with respect to very low-acceleration transfers are shown to be small.