Basic parameters for low thrust mission and system analysis.

Abstract

Development of a basic set of normalized parameters to represent low-thrust system characteristics. The conditions which must be met to obtain trajectory and performance data which are invariant with the launch vehicle characteristics, the selected power, the specific mass of the low-thrust vehicle, and the efficiency of the ion propulsion system are derived. This normalized representation of mission characteristics frees the analyst from having to rerun the trajectories if any of the aforementioned parameters are varied. Examples pertaining to a low-thrust Jupiter flyby and comet Encke rendezvous are given to demonstrate the utility of the method of presentation.