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Design of an Advanced Two-Phase Capillary Cold Plate
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Abstract
In the design of advanced two-phase capillary pumped loop heat transport systems for Space Station elements, evaporator plates able to accommodate a wide variety of instruments/payloads are becoming critical items. An evaporator plate configuration consisting of six parallel capillary evaporator pumps bonded into a common aluminum cold plate has been selected under a NASA Goddard Space Flight Center (GSFC) Focussed Technology program.* Predicted performance characteristics include a power density capability greater than 10 W/cm2, a transport capacity of over 5 kW (per 900 cm2 plate), turndown capability of over 16:1, and load-sharing capability (within a closed system). Following proof-of-performance tests, these plates will form part of a thermal test bed at NASA/GSFC. This paper details the design and analysis of the prototype capillary cold plates along with the proposed fabrication and test plans. Although the first prototype capillary cold plate (PCCP) unit is under construction, it seems that the present PCCP baseline design will meet the specified requirements. A section is also devoted to the evaluation of payload accommodation aspects and future design evolution of capillary pumped loop two-phase evaporator plates.
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Chalmers, D., Kroliczek, E., and Ku, J., "Design of an Advanced Two-Phase Capillary Cold Plate," SAE Technical Paper 861829, 1986, https://doi.org/10.4271/861829.Also In
References
- Kroliczek E. Ku J. Ollendorf S. “Design, Development and Test of a Capillary Pump Loop Heat Pipe,” AIAA-84-1720 June 1984
- Proceedings from “Capillary Pumped Loop Technology Workshops,” OAO Corporation July 1985 Aerospace Corporation January 1986
- Ku J. et al. “Functional and Performance Test of Two Capillary Pumped Loop Engineering Models,” AIAA-86-1248 June 1986
- Ku J. et al. “Capillary Pumped Loop GAS and Hitchhiker Flight Experiments,” AIAA-86-1249 June 1986
- “Space Station Mission Requirements Data Base,”
- Presentations made at the Space Station Advanced Development: Thermal Control Meeting December 2-6 1985 NASA/JSC
- Chalmers D. R. et al. “Application of Capillary Pumped Loop Heat Transport Systems to Large Spacecraft,” AIAA-86-1295 June 1986