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A Two-Phase Thermal Management System for the Space Station
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English
Abstract
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.
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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.Also In
References
- A Pumped Two-Phase Cooling System for Spacecraft Ollendorf S. Costello F. SAE 831099
- Thermal Management System Technology Development for Space Station Applications Rankin G. Marshall P. SAE 831097
- Space Constructable Radiator Prototype Test Program Alario J. Brown R. Otterstedt P. AIAA-84-1793
- Integration and Flight Demonstration of a High Capacity Monogroove Heat-Pipe Radiator Rankin J.G. AIAA-84-1716
- A Contact Conductance Interface for a Space Constructable Heat pipe Radiator Oren J. Fleming M. SAE 831101
- A Two-Phase Thermal Management System for Large Space Platforms Bland T.J. Downing R.S. Rogers D.P. AIAA-84-1758