Abstract
A self-contained navigation scheme is described and analysed for the case of an unmanned spaceship launched from Earth and established in a free-fall solar orbit that passes within a few thousand miles of another planet and subsequently returns to Earth. A statistical study of the navigation errors and the micro-rocket fuel requirements is made, using a three-dimensional model of the solar system. Several different trajectories are subjected to a systematic study to determine the optimum times at which positional checks and velocity corrections should be made in order to minimize both the amount of fuel required and the errors in passing distance at the target planet and miss distance upon return to Earth.
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