Two separate design approaches are reported for a pumped loop radiator used to transfer heat from the cold end of a solar-dynamic-powered Stirling engine. The first approach uses a standard method to determine radiator requirements to meet specified end-of-mission conditions. Results of trade-off studies conducted for the analysis are included. Justification of this concept within the specified parameters of the analysis is provided. The second design approach determines the life performance of the radiator/Stirling system. In this approach, the system performance was altered by reducing the radiator heat transfer area. Performance effects and equilibrium points were determined as radiator segments were removed. This simulates the effect of loss of radiator sections due to micrometeoroid and space debris penetration. The two designs are compared on the basis of overall system requirements and goals.
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