Technology Development for In-space Nuclear Electric Propulsion

Nuclear electric propulsion (NEP)-powered vehicles have been contemplated for human Mars

missions. The nuclear power system contemplates using a high temperature light-weight nuclear reactor

for the production of electrical power in the range of 2-5 MWe with a 3-10 year service life. A myriad of

technology options exist that could potentially achieve these mission objectives. Significant technology

development is required to narrow the field of design options that could be used for a NEP-powered

vehicle.

The NEP system is comprised of five major critical technology elements: the nuclear power source,

the system to convert thermal power into electrical power, a large radiator to serve as the cold-side of the

power conversion thermodynamic cycle, the electric propulsion system, and a power management and

distribution system that will deliver the power to the propulsion system and provide required electrical

isolation between different components. At the system level, each of these technology elements must

operate in concert. For example, system extracting heat from the nuclear reactor must be compatible

with the input required for the power conversion system. NASA’s Space Nuclear Propulsion (SNP)

project has conducted a number of technical interchange meetings to survey technology options for each

critical element.

In this presentation, we discuss the current state-of-the-art for each sub-system and the options that

the SNP NEP team has identified for potential parallel-path development and technology maturation. The

development path for each technology is distinct, and involves hardware development and testing

supported by significant modeling and simulation of each element.