Thermal management of instruments on space platforms using a high capacity two-phase heat transport systemA system utilizing a pumped, two-phase single component working fluid for heat exchange and transport services necessary to meet the temperature control requirements of typical orbiting instrument payloads on space platforms is described. The design characteristics of the system is presented, together with a presentation of a laboratory apparatus for demonstration of proof of concept. Results indicate that the pumped two-phase design concept can meet a wide range of thermal performance requirements with the only penalty being the requirement for a small liquid pump.
Document ID
19820058588
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Ollendorf, S. (NASA Goddard Space Flight Center Greenbelt, MD, United States)
Fowle, A. (NASA Goddard Space Flight Center Greenbelt, MD, United States)
Almgren, D. (Arthur D. Little, Inc. Cambridge, MA, United States)