Nuclear Thermal Rocket and Arc Jet Integrated System Modeling

To further improve achievable Isp for NTR systems, a method is proposed to augment propellant heating with an arcjet or magnetohydrodynamic (MHD) system. In this rocket cycle, the propellant gains energy in the reactor as usual, however, instead of being exhausted through a nozzle, the propellant is (1) introduced directly into a large turbopump assembly, (2) directed back through the reactor core, and (3) finally directed into the arcjet or MHD thruster. This hybrid system approach can provide very high propellant temperatures and higher Isp. A detailed system analysis will be accomplished to determine the benefits and performance of a hybrid NTR/Arc Jet system. The outcomes will be (1) a system model adaptable for specific mission analysis and (2) detailed analysis for developing such a hybrid system.

Investigate an innovative hybrid system for improved performance of a nuclear thermal propulsion vehicle. Seek to improve feasibility of manned Mars missions and other deep space missions by reducing transit time and crew radiation exposure.

This is early/mid-stage (TRL 3) — the most realistic path in is NASA SBIR/STTR, which funds small businesses and research institutions to develop technology aligned with NASA's needs (equity-free, phased funding). Check whether a current SBIR/STTR solicitation topic overlaps with this project's technology area, or contact the project directly (above) to ask.

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