Development of the Internal Thermal Control System (ITCS) for International Space Station (ISS)
Date Published: 2001-07-09
Paper Number:2001-01-2332
DOI: 10.4271/2001-01-2332
Citation:
Patel, V., Barido, R., Johnson, B., and Ibarra, T., "Development of the Internal Thermal Control System (ITCS) for International Space Station (ISS)," SAE Technical Paper 2001-01-2332, 2001, doi:10.4271/2001-01-2332.
The International Space Station (ISS) internal thermal control system (ITCS) has been developed jointly by the Boeing Corporation, Huntsville, Alabama, and Honeywell Engines & Systems, Torrance, California, to meet ISS internal thermal control needs. The ITCS provides heat removal for the critical life support systems and thermal conditioning for numerous experiment racks. The ITCS will be fitted on a number of modules on the ISS. The first module, the US Laboratory Module, was launched in February 2001 and is now operational on the ISS.
The dual loop system is comprised of a low-temperature loop (LTL) and a moderate-temperature loop (MTL). Each loop has a pump package assembly (PPA), a system flow control assembly (SFCA), a three-way mixing valve (TWMV), several rack flow control assemblies (RFCA), cold plates, pressure sensors, temperature sensors, a pump bypass assembly (PBA), and a heat exchanger. In addition, the MTL has an additional TWMV, a payload regeneration heat exchanger (P/RHE) and a manual flow control valve (MFCV). The LTL has a service performance and checkout unit (SPCU) heat exchanger. The two loops are linked via one loop crossover assembly (LCA) providing cross loop capabilities and a single-PPA two-loop functionality.
Honeywell Engines & Systems performed extensive qualification testing at the component level. The Boeing Company performed the system level qualification testing. Details of the system testing and verification are contained in Reference
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