A Two-Phase Thermal Management System for the Space Station 841525
The central thermal management system for the proposed NASA Space Station will likely employ a two-phase thermal bus to satisfy the high power and long transport distance requirements. Significant potential weight and power savings accrue from this approach. A pumped two-phase cooling loop is described that can meet the requirements while maintaining constant heat source temperatures with large power and sink temperature turndown capability. Predicted performance of the 25 kW ammonia flight conceptual design is presented along with test results from a Freon 114 test loop which confirms predicted characteristics.
Citation: Bland, T., Downing, R., and Rogers, D., "A Two-Phase Thermal Management System for the Space Station," SAE Technical Paper 841525, 1984, https://doi.org/10.4271/841525. Download Citation
Author(s):
Timothy J. Bland, Robert S. Downing, David P. Rogers
Affiliated:
Sundstrand Advanced Technology Group, Sundstrand Corp., Rockford, IL
Pages: 10
Event:
Aerospace Congress and Exposition
ISSN:
0148-7191
e-ISSN:
2688-3627
Also in:
Space Systems Technology-SP-0593
Related Topics:
Spacecraft
Thermal management
Energy conservation
Buses
Refrigerants
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