This study was part of a broader assessment of ground testing facility technology development at Stennis Space Center for testing non-nuclear thermal propulsionsub-scale systems. One specific technology need was the ability to provide high temperature hydrogen, above the auto ignition temperature of 1390 R, at a flow rate as high as 2.2 lb/sec and for a duration of five minutes. Assessment of five concepts was performed and included: the High Heat Flux Rig, the Hydrogen Wave Heater, the VTX HyHeat combustion chamber, fuel-air burners, and an electric resistance heater. Of the five concepts assessed, the more conventional Fuel-Air Burner was identified as the best near-term solution for testing at the E-Complex at SSC. With the exception of the Electric-Resistance Heater concept, all concepts were also identified as feasible, some with stipulations.

The development of a nuclear thermal propulsion (NTP) engine for manned spaceflight missions to Mars and other distant exploration sites will require a ground test facility that is capable of test firing the engine safely and with zero harmful emissions. This project examined several design concepts for such a NTP ground test facility. These include, but were not limited to, borehole, scrubber and total-containment systems.

The project built, installed, and tested a novel data acquisition and control system by combining two independent architectures into one standalone unit. The simplified architecture reduces component numbers while maintaining the strict hardware reliability demands and high mean time between failures. Implementation of this technology potentially reduces hardware and software costs as it relates to the operation of a control center. This project demonstrated two immediate and significant benefits to NASA:

1. Development of a novel data acquisition and controls architecture that does not rely on PLCs thus improving control loop rate speed.

2. Creation of a separate, stand alone, data acquisition and control system for use on small scale projects that are independent of the test complex acquisition and control systems.

NTP engine exhaust, hot gaseous hydrogen is nominally expected to be free of radioactive byproducts from the nuclear reactor; however it has the potential to be contaminated due to off-nominal engine reactor performance and therefore prevents its free venting to the atmosphere. This project evaluated two options for gaseous O2 retention: (1) compression and (2) liquefaction. After comparison studies were performed it was determined the liquid storage option is recommended based on storage tank volume, cost, risk and safety considerations. The liquid storage option has no mechanical moving parts and operates at low pressure compared to the gas storage.

Nuclear Thermal Propulsion is an option for NASA to extend humanities reach to destinations such as Mars. The goal of this project was to develop preliminary design elements and integrated systems for making a proof-of-concept technology demonstrator subscale system for a non-nuclear rocket engine. The results of this project identified a design concept for a non-nuclear subscale demonstrator at SSC's E3 test stand. In addition the project determined the physical arrangements required at E3 while refining the cost and schedule estimates for design, build and execution of a subscale technology demonstrator project.