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Design of Refractory Metal Life Test Heat Pipe and CalorimeterHeat pipe life tests have seldom been conducted on a systematic basis. Typically, one or more heat pipes are built and tested for an extended period at a single temperature with simple condenser loading. Results are often reported describing the wall material, working fluid, test temperature, test duration, and occasionally the nature of any failure. Important information such as design details, processing procedures, material assay, power throughput, and radial power density are usually not mentioned. We propose to develop methods to generate carefully controlled data that conclusively establish heat pipe operating life with material-fluid combinations capable of extended operation. The test approach detailed in this Technical Publication will use 16 Mo-44.5%Re alloy/sodium heat pipe units that have an approximate12-in length and 5/8-in diameter. Two specific test series have been identified: (1) Long-term corrosion rates based on ASTM-G-68-80 (G-series) and (2) corrosion trends in a cross-correlation sequence at various temperatures and mass fluences based on a Fisher multifactor design (F-series). Evaluation of the heat pipe hardware will be performed in test chambers purged with an inert purified gas (helium or helium/argon mixture) at low pressure (10-100 torr) to provide thermal coupling between the heat pipe condenser and calorimeter. The final pressure will be selected to minimize the potential for voltage breakdown between the heat pipe and radio frequency (RF) induction coil (RF heating is currently the planned method of powering the heat pipes). The proposed calorimeter is constructed from a copper alloy and relies on a laminar flow water-coolant channel design to absorb and transport energy
Document ID
20100029805
Acquisition Source
Marshall Space Flight Center
Document Type
Technical Publication (TP)
Authors
Martin, J. J.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Reid, R. S.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Bragg-Sitton, S. M.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Date Acquired
August 25, 2013
Publication Date
August 1, 2010
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NASA/TP-2010-216435
M-1284
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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