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This paper presents the development of a Thermal Math Model (TMM) of the space station U.S. Laboratory-A module. The TMM is used to predict operating thermal environments for all interior and exterior areas of the laboratory module. The model was constructed as a tool for performing developmental design analyses providing payload designers and analyzers a means for accurately predicting payload environments. The TMM determines the overall effect of a payload rack on neighboring subsystem and payload racks, standoffs, endcone regions, and the module cabin. The TMM has also been used to assess the percentage of Internal Thermal Control System (ITCS) cooled electronic equipment input power that dissipates to the module cabin air system. Active and passive thermal systems of the laboratory module are integrated in the TMM, providing the capability of predicting the interaction of the two thermal systems.