Mars ascent concept using NTR with lithium propellant

What is it about?

We present a concept for using solid lithium as propellant in a Nuclear Thermal Rocket (NTR). Lithium propellant avoids some drawbacks of hydrogen propellant for nuclear rockets on long duration missions. We discuss the advantages and disadvantages of lithium as propellant, describe a notional Mars lander using this concept in the ascent stage, and compare the mass of this notional system to the mass of Mars landers with various other non-nuclear and nuclear propulsion systems. The mass of the Mars lander with some lithium NTR options is found to be comparable to the mass of a lander with a hydrogen NTR system. We also discuss areas where further study is needed to determine whether lithium NTR is actually feasible.

Featured Image