Application of nuclear electric propulsion to manned Mars missions.

Abstract

This paper presents some interim results of a continuing feasibility study of a manned Mars landing mission using a combination of nuclear rocket and nuclear electric propulsion. These include 1) an analytical tool for simultaneously optimizing the vehicle design and its associated trajectory, 2) a typical resultant vehicle/trajectory concept, and 3) preliminary parametric performance data. The results indicate that a straightforward vehicle design using standard Saturn V launch vehicles is reasonably feasible. The required initial mass in Earth orbit lies between 400,000 and 900,000 kg; depending on trip time, Earth return conditions, and powerplant specific weight. An electrical power of 3-8 Mw is required at a powerplant specific weight of 10-20 kg/kw.