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Radiator for Nuclear Powered Spacecraft, Year 2

Completed TRL 5 (started at 3, targeting 5)

Description

Advanced power conversion technologies will require high operating temperatures and would benefit from lightweight radiator materials. Radiator performance dictates power output for nuclear electric propulsion systems. Pitch-based carbon fiber materials have the potential to offer significant improvements in operating temperature, thermal conductivity, and mass. These properties combine to allow significant decreases in the total mass of the radiators and significant increases in the operating temperature of the fins.

Benefits

Woven bare carbon fins are applicable to all future missions using nuclear electric power and propulsion and to some solar system planetary surface missions using nuclear power generation systems. The bare carbon fins have the potential, by reducing the size and mass of the radiator system, to be enabling for NEP.

Details

Technology areaThermal Management Systems > Thermal Control Components and Systems > Heat Rejection and Storage
ProgramCenter Innovation Fund: MSFC CIF (MSFC CIF)
Lead organizationMarshall Space Flight Center, Huntsville, AL
Start date2013-10-01
End date2014-09-30

Project contacts

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How to get involved

This is early/mid-stage (TRL 5) — 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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