Abstract
In this paper, a thermal control system, using loop heat pipe as basic heat transfer elements, was designed for Alpha Magnetic Spectrometer. A system level model, which is integrated with the International Space Station model, was built, optimized and used to analyze several typical cases representing the orbital environment, to understand the operation of the LHP-based thermal control system during the mission time. The LHP system was proved to be able to maintain the Cryocooler within the required temperature range in most cases, while under some worst cold environments, the bypass valve needs to be activated.
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