49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference · 2013 · 28 citations · 3 references
EngineeringComputational EngineeringNuclear EngineeringNuclear MaterialsNuclear PhysicsPropulsionNuclear Fuel MaterialsNuclear PropulsionReactor Core DesignReactor DesignReactor KineticsThermal Reactor PhysicsEngine Thrust PerformanceNuclear Rocket PropulsionNumerical SimulationPower DepositionPower Deposition ProfilesPropulsion System SimulationReactor Core ModelingSpecific Impulse
Nuclear thermal rockets trace back to the NERVA program’s ZrC‑graphite composite and later CERMET fuel designs. Four NPSS models—two ZrC‑graphite and two CERMET—represent small and large engines using RL‑10 and RL‑60 turbomachinery maps, with thrusts of ~33.4 kN and ~111.2 kN, and reactor power profiles derived from MCNP5 simulations. The study evaluates thermodynamic state points, thrust, specific impulse, reactor power, and peak fuel temperature for each engine design.
Four nuclear thermal rocket (NTR) models have been created in the Numerical Propulsion System Simulation (NPSS) framework. The models are divided into two categories. One set is based upon the ZrC-graphite composite fuel element and tie tube-style reactor developed during the Nuclear Engine for Rocket Vehicle Application (NERVA) project in the late 1960s and early 1970s. The other reactor set is based upon a W-UO2 ceramic- metallic (CERMET) fuel element. Within each category, a small and a large thrust engine are modeled. The small engine models utilize RL-10 turbomachinery performance maps and have a thrust of approximately 33.4 kN (7,500 lbf ). The large engine models utilize scaled RL-60 turbomachinery performance maps and have a thrust of approximately 111.2 kN (25,000 lbf ). Power deposition profiles for each reactor were obtained from a detailed Monte Carlo N-Particle (MCNP5) model of the reactor cores. Performance factors such as thermodynamic state points, thrust, specific impulse, reactor power level, and maximum fuel temperature are analyzed for each engine design.
3