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A high power spacecraft thermal management systemThis paper describes the design and test results of an ammonia hybrid capillary pumped loop thermal control system. As a hytbrid, the system can operate as either a passive, capillary pumped loop, or, as a mechanically pumped system. The system is comprised of an evaporator section, a condenser section, 10 meters of liquid and vapor transport lines, a mechanical pump, and a reservoir. In the evaporator section, four capillary pumps are each integrated into three cold plates. The mechanical pump is installed in the liquid line and is in series with the capillary pumps. Testing has demonstrated that in the capillary pumped mode, the HPSTM can acquire and transport a total heat load of between 120 W and 24 kW, with a maximum heat flux density of 4.3 W/sq cm in the evaporator section. In the mechanically pumped configuration, a heat acquisition potential of 50 kW (9 W/sq cm heat flux density) has been demonstrated. The hybrid system still retains the proven capillary capabilities of temperature control, heat load sharing and fluid flow control between evaporator plates, rapid power cycling, and pressure priming recovery of deprimed evaporators.
Document ID
19880056527
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Ku, J.
(OAO Corp. Greenbelt, MD, United States)
Kroliczek, E. J.
(OAO Corp. Greenbelt, MD, United States)
Mccabe, M. E., Jr.
(NASA Goddard Space Flight Center Greenbelt, MD, United States)
Benner, S. M.
(TS Infosystems, Inc. Lanham, MD, United States)
Date Acquired
August 13, 2013
Publication Date
June 1, 1988
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 88-2702
Accession Number
88A43754
Distribution Limits
Public
Copyright
Other

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