Vehicle and Trajectory Optimization of Nuclear Electric Propulsion spacecraft for Lunar Missions

摘要

A new combined vehicle and trajectory optimization problem is solved for a low-thrust nuclear electirc propulsion spacecraft. The problem involves computing the optimal spacecraft sizing parameters and trajectory design variables which result in the maximum payload for a fixed trip time, planar transfer from circular low-Earth orbit to circular low-lunar orbit. In particular, optimal specific impulse and input power are computed. The detailed vehicle and trajectory optimization approach is effective in solving a complex, interactive problem that is important to both spacecraft and mission designers. Several numerical solutions are obtained for a wide range of trip times.