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Heat Pipe Technology for Current Spacecraft and High Power Thermal Management
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English
Abstract
The application of conventional axially grooved heat pipes to the thermal control of attached shuttle payloads, instruments on free flyers, communications satellites and body mounted radiators for space station common modules is discussed. Also presented is the evolution of an advanced axially grooved design for application to the space station's space erectible radiators (SERS). Capillary Pumped Loop (CPL) development status and its application to high power thermal management for space station applications are also included.
Authors
Citation
Kroliczek, E. and Brennan, P., "Heat Pipe Technology for Current Spacecraft and High Power Thermal Management," SAE Technical Paper 851353, 1985, https://doi.org/10.4271/851353.Also In
References
- Harwell, B. Edelstein, F. “Advanced Thermal Control Techniques for Emerging Communications Satellites” AIAA Paper No. 84-1774 June 1984
- Brennan, P. et. al. “Thermal Design of Current Spacecraft and Shuttle Payloads Utilizing Heat Pipe Technology” AIAA Paper No. 35-1008 June 1985
- Berger, M. E. Delly, W. H. “Application of Heat Pipes to the ATS-F Spacecraft” ASME Paper No. 73-ENAs-46 July 1973
- Rankin, J.G. “Integration and Flight Demonstration of a High-Capacity Monogroove Heat-Pipe Radiator” Paper No. 84-1716. AIAA 19th Thermophysics Conference Snowmass, Colorado June 25-28 1984
- Kroliczek, E.J. Kit, J. Ollendorf, S. “Design, Development and Test of a Capillary Pump Loop Heat Pipe” Paper No. 84-1720. AIAA 19th Thermophysics Conference Snowmass, Colorado June 25-28 1984
- “Capillary Pumped Loop (CPL) Development Status Report” Report to NASA/Goddard Space Flight Center by OAO Corporation January 1985