Analytical techniques presented permit calculation of heat transfer rates with various thermal protection systems for tanks subjected to on-board, solar, and planetary heat fluxes; effectiveness of systems in reducing propellant heating is shown for ideal heat transfer models and simplified hydrogen oxygen terminal stage used for typical Mars missions.
Analysis of thermal-protection systems for space-vehicle cryogenic-propellant tanks
NASA -- Tech Report
1962
92 pages
Report
Englisch
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Lightweight Thermal Protection Systems for Space Vehicle Propellant Tanks
SAE Technical Papers | 1964
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