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Articulated Heat Pipe Concepts and Developments
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Abstract
Reliable, low mass rotating heat transfer joints using heat pipes have many potential on-board spacecraft applications including hinges, rotating platforms and moveable radiators. These joints require a high thermal conductance and low outgassing and fluid leakage rates to prevent spacecraft contamination. This paper describes two concepts: the first has the joint in the heat pipe envelope; the second utilizes a high thermally conductive fluid in a gap between two separate heat pipes, one located inside the other.
The second concept has been pursued through the testing of a developmental heat pipe-to-heat pipe joint. Thermal performance up to 1500 watts showed a joint thermal resistance of 0.008 to 0.01 C/watt (thermal conductance of 100-125 watts/C) in the temperature range of 25-50 C. Theoretical calculations show the gap fluid leakage to be less than 1 × 10−5 grams of NaK in five years. Extended rotary life test, seal design, fluid leakage measurement and improved heat pipe performance are areas of future development.
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Authors
Citation
Ernst, D. and Shaubach, R., "Articulated Heat Pipe Concepts and Developments," SAE Technical Paper 831102, 1983, https://doi.org/10.4271/831102.Also In
References
- Wiggens J. A. Vought C. L. “Design Analysis for Surveillance Satellite Thermal Control System” OREN Wiggens & Vought Corporation Dallas, Texas AFFDL-TR-79-3009
- “Development of a Cryogenic Rotating Heat Pipe Joint” Final Report, Rockwell International, SD78-AP-0124, Contract NASA-9726 September 1978
- Ernst D. M. “Heat Pipes for NEP Spacecraft” Thermacore, Inc. Lancaster, PA 16th IECEC Conference, Atlanta, GA, JPL Subcontract 955100 and 955935 August 1981
- Contract #F33615-31-C-3413 Wright-Patterson Air Force Base
- Final Report, JPL Subcontract 955935