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Development Status of a Two-Phase Thermal Management System for Large Spacecraft
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English
Abstract
An update of a Two-Phase Thermal Management System concept is presented including hardware status for flight prototypic components, modeling techniques, and terrestrial test results for both preprototype and some prototypic hardware. A test plan for a microgravity test on a KC 135 is discussed.
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Citation
Bland, T., Chen, I., and Hill, D., "Development Status of a Two-Phase Thermal Management System for Large Spacecraft," SAE Technical Paper 861828, 1986, https://doi.org/10.4271/861828.Also In
References
- Bland, T. J. Downing, R. S. Rogers, D. P. “A Two-Phase Thermal Management System for Large Space Platforms.” AIAA-84-1758
- Bland, T. J. Downing, R. S. Rogers, D. P. “A Two-Phase Thermal Management System for the Space Station.” SAE 841525
- Bland, T. J. Downing, R. S. Rogers, D. P. “A Two-Phase Thermal Management System for Large Spacecraft.” SAE 851351
- Niggemann, R. E. Greenlee, W. J. Hill, D. G. Ellis, W. Marshall, P. “A Swirl Flow Evaporative Cold Plate.” AIAA-85-0920