Two-Phase Thermal Control Technology for Small Spacecraft Exploration

The challenge of this task is to provide an order of magnitude reduction in thermal control power using half the mass while accommodating high heat fluxes and milli-Kelvin stability required for enhanced science.

This task will develop a 2-φ mechanically pumped fluid loop thermal control system for small spacecraft that minimizes system resources, manages spacecraft temperatures, reclaims and redistributes waste heat, and provides science-enabling thermal stability.

This technology •Provides order of magnitude reduction in TCS power and 50% reduction in mass over current state-of-the-art. •Accommodates high heat fluxes up to 5 W/cm²; isothermalization of < 2 ^oC over a 1-m payload bench; temporal stability of < 0.05 ^oC/minute. •Modular, scalable, configurable to enable integration and at reduced costs. High degree of control authority results in less thermal vacuum testing time.

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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