Feasibility of Isotopic Power for Manned Lunar Missions. Volume 1. Summary. Page: 32 of 61
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TABLE 2 (continued)
Duct heat losses
Design Achieved as of
Approach to Achieve
Design indicates can be
State of the art
Heat source Weight
changer High temperature
cladding on fins
Energy con- Alternator (P-M
version- type) efficiency
Valves and Recuperator
ducts bypass valve
Achieved in pro-
Not measured as
Achieved in pro-
Reduce to 1140* F to solve fuel block
temperature problem. High efficiency
Function of radiator
High with roller
45,000 rpm Achieved
System efficiency dependent on
compressor efficiency. May
present development problem in
matching compressor to turbine
at lower temperature operation.
Roller bearings OK for 14-day
Gas bearings for longer life; de-
Recuperator parameters change
for lower temperature operation.
Accuracy of sensor and positioner
may require development.
Simple on-off system; no problem
Prototype system No problem
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Feasibility of Isotopic Power for Manned Lunar Missions. Volume 1. Summary., report, January 1, 1964; Baltimore, Maryland. (https://digital.library.unt.edu/ark:/67531/metadc1032333/m1/32/: accessed May 24, 2019), University of North Texas Libraries, Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.