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The U.S./International Space Station will be assembled incrementally using nineteen flights of the National Space Transportation System (NSTS) Space Shuttle to complete the configuration. This process will produce nineteen different spacecraft configurations, each of which must perform as a fully functional, independent space vehicle. This results in unique design requirements on station distributed systems necessary to allow incremental system buildup while providing some minimum capability early in the assembly sequence. The Thermal Control System (TCS), like electrical power, attitude control, and communications must be present on the initial flight configuration and must grow in capability as assembly continues. This paper summarizes the Space Station program requirements for the TCS, and outlines the capabilities of the TCS for each assembly configuration.