Assessment of Electric-Pump-Fed Nuclear Thermal Propulsion for Near-Term Missions

Abstract

This paper describes an analysis of the viability of electric-pump-fed nuclear thermal propulsion (EPFS NTP) for space missions. EPFS is an alternative to the turbopumps typically employed by high-impulse rocket engines, but it is not yet clear if they are suitable for this application. The method employed by this analysis utilizes the rocket equation to determine whether EPFS NTP spacecraft are capable of delivering payloads to Jupiter and Saturn, subject to the mass and geometry constraints imposed by near-term launch vehicles. The analysis found that 7.5 klbf EPFS NTP can deliver up to 3000 kg to Jupiter and 2000 kg to Saturn, and that spacecraft with higher thrust EPFS NTP engines deliver smaller payloads. This analysis provides confidence that EPFS NTP can enable a space mission of interest, and therefore EPFS can be considered as an alternative to turbomachinery for near-term NTP engine development.