A Comparative Analysis of Ion and Nuclear Thermal Propulsion Systems for Deep Space Missions

Abstract

This research paper provides a side-by-side comparison of Ion and Nuclear Thermal Propulsion technologies through theoretical modeling and numerical simulations. The study has been able to pinpoint the tradeoffs in operational parameters between high-efficiency, low-thrust ion systems and high-thrust, moderate-efficiency nuclear systems by examining specific impulse, thrust, efficiency, and other relevant parameters. The findings reveal that there is a significant relationship between specific impulse and propellant economy, thus endorsing a hybrid propulsion system as a viable option for interstellar missions.