Computational Materials/Engineering Enabling Interstellar Probe Feasibility

This work will identify material concepts and access manufacturing/scaling of architectures that can operate in the extreme solar radiation environment (>3000 C) and are compatible with STP propellants. Sizing of C/C will be conducted to determine thicknesses of C/C required to manage any recession due to heating in the solar radiation environment, both externally but also internally to the heat exchanger when in contact with propellants.

New material concepts/ architectures are required to implement Solar Thermal Propulsion (STP) technology, which offers the potential to greatly diminish the transit times required to reach the interstellar medium, from 40 years for Voyager (SOA) to 8-10 years, making dedicated scientific investigation practical. Advanced coatings that would enable solar thermal propulsion by withstanding high temperature hydrogen were investigted using integrated computational materials and engineering techniques ranging from the atomisitic scale to the macroscale.

This is early/mid-stage (TRL 2) — 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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