Nuclear Electric Propulsion for Uranus Missions Parametric Assessment

Nuclear Electric Propulsion (NEP) is an exciting technology that has potential to enable low-thrust missions to Uranus that are otherwise impossible using traditional chemical propulsion. NEP provides enhanced mission flexibility by opening launch windows for such missions and can improve the mass available for payload or propellant at destination while providing power for use in propulsion and communications. This paper investigates the mission trade space, illustrates the tradeoff between time of flight and the usable mass at destination, and considers the effect of different NEP system mass per power on mission performance and optimal propulsion power. The lower-performing NEP systems deliver a comparable mass to Uranus as Uranus Orbiter Probe study from NASA’s Decadal Survey, around 250 kg. The higher-performing NEP systems enable payloads up to 1,250 kg which is sufficient for extensive maneuvering in the Uranus system but could also be used for scientific instruments.