AAS 95-399

Optimal Earth-Moon Trajectories Using Nuclear Electric Propulsion

C. A. Kluever, University of Missouri-Columbia/K.C., MO, B. L. Pierson, Iowa State University, Ames, IA

Abstract

Minimum-fuel, 2-D and 3-D, Earth-moon trajectories are obtained for a nuclear electric propulsion spacecraft. The initial and terminal states are low, circular parking orbits about the Earth and moon. The trajectory has a fixed thrust-coast-thrust engine sequence and is governed by the classical restricted three-body problem dynamic model. An analytical expression for quasi-circular low-thrust transfers is used to approximate and replace the hundreds of initial and final orbits about the Earth and moon. Numerical results are presented for the optimal Earth-moon trajectories.