Assessment of the Technical Characteristics of a Capillary Evaporator in Microgravity (Cemex) - 01.09.14
Science Objectives for Everyone CEM will test two capillary evaporators, the main part of the two-phase heat transfer loops used for thermal control in spacecraft.
Science Results for Everyone Information Pending
Sponsoring Space Agency
Russian Federal Space Agency (Roscosmos)
ISS Expedition Duration
April 2006 - September 2006
Previous ISS Missions
Performance of thermodynamic analysis and assessment of the technical characteristics of the capillary evaporator. Assessment of proposed technologies of evaporators for future application in space conditions.
Capillary evaporator test performance aboard the ISS RS. The experimental equipment is a monoblock and consists of a capillary evaporator configured as a circuit (CPL1) and an electronic control unit. The capillary evaporator design uses a two-phase heat transfer loop, which is used to support satellite thermal control. The loop consists of an evaporator, cooler and reservoir connected by pipes. The heat generated in the evaporator is transferred by working fluid to the cooler section. The reservoir supports the temperature inside the loop and the required reserves of working fluid. The fans provide cooling of the capacitor. The electronic unit consists of a computer with a single-board microprocessor for data acquisition and regulation of the capillary evaporator power, as well as for setting an operating temperature in the reservoir. Water in amount of 20 ml will be used as a coolant.
Kit with CEM equipment consisting of the CPL block and Memory map CEM* (in cover). Image courtesy of Russian Space Agency (FSA).
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