A spacecraft thermal control system must keep the cabin and electronic equipment within operational temperature ranges by transporting heat out of the spacecraft. This process is generally accomplished via a series of air-to-liquid heat exchangers with ultimate dissipation to space via radiator panels. In contrast, a proposed self-regulating freezable heat exchanger is designed to passively maintain and regulate thermal control through water ice buildup within the heat exchanger structure. In order to determine the feasibility and effectiveness of this technology, an integrated analysis of the thermal loads encountered by an orbital spacecraft was conducted. The analysis determines the expected internal and external heat loads on the spacecraft, outlines potential implementation of the hardware into the thermal control system, and predicts the expected performance of the technology. The results attained partially validate the capability of the self-regulating freezable heat exchanger to reject the anticipated range of heat loads.
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