Feasibility of Isotopic Power for Manned Lunar Missions. Volume 1. Summary. Page: 30 of 61
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TABLE 2 (continued)
Heat rejec- Radiator reliability
tion system (14 d)
Coolant pumps re-
liability (14 d)
Area for 1500-
watt (e) system*
Overall System efficiency
(end of life)
Design Achieved as of
0 5 psi
Vehicle skin suf-
0.9999 by redun-
fect on system
PbTe = 255 ft2
Approach to Achieve
Calculations based on NASA data.
Single pump = 0.991 based on Titan
and Minuteman data.
Achieved by ord-
nance and tem-
could be accom-
Requirement does not affect mission
success or crew safety, primarily
general isotope safety criteria.
PbTe gives 6.69%.
PbTe gives 432 lb.
*Development problems--see text.
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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/m1/30/: accessed May 27, 2019), University of North Texas Libraries, Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.