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Closeout Report for the Refractory Metal Accelerated Heat Pipe Life Test ActivityWith the selection of a gas-cooled reactor, this heat pipe accelerated life test activity was closed out and its resources redirected. The scope of this project was to establish the long-term aging effects on Mo-44.5%Re sodium heat pipes when subjected to space reactor temperature and mass fluences. To date, investigators have demonstrated heat pipe life tests of alkali metal systems up to .50,000 hours. Unfortunately, resources have not been available to examine the effect of temperature, mass fluence, or impurity level on corrosion or to conduct post-test forensic examination of heat pipes. The key objective of this effort was to establish a cost/time effective method to systematically test alkali metal heat pipes with both practical and theoretical benefits. During execution of the project, a heat pipe design was established, a majority of the laboratory test equipment systems specified, and operating and test procedures developed. Procurements for the heat pipe units and all major test components were underway at the time the stop work order was issued. An extremely important outcome was the successful fabrication of an annular wick from Mo-5%Re screen (the single, most difficult component to manufacture) using a hot isostatic pressing technique. This Technical Publication (TP) includes specifics regarding the heat pipe calorimeter water-cooling system, vendor design for the radio frequency heating system, possible alternative calorimeter designs, and progress on the vanadium equilibration technique. The methods provided in this TP and preceding project documentation would serve as a good starting point to rapidly implement an accelerated life test. Relevant test data can become available within months, not years, and destructive examination of the first life test heat pipe might begin within 6 months of test initiation. Final conclusions could be drawn in less than a quarter of the mission duration for a long-lived, fission-powered, deep space probe.
Document ID
20130010052
Acquisition Source
Marshall Space Flight Center
Document Type
Technical Publication (TP)
Authors
Martin, J.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Reid, R.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Stewart, E.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Hickman, R.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Mireles, O.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Date Acquired
August 27, 2013
Publication Date
January 1, 2013
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
M-1353
NASA/TP-2013-217477
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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