Analytical techniques are presented that permit the calculation of heat-transfer rates with various thermal-protection systems for liquid-cryogenic-propellant tanks subjected to on-board, solar, and planetary heat fluxes . The effectiveness of these protection systems in reducing propellant heating is shown both for ideal heat-transfer models and for a simplified hydrogen-oxygen terminal stage used for typical Mars missions.
Analysis of Thermal-Protection Systems for Space-Vehicle Cryogenic-Propellant Tanks
01.01.1962
Sonstige
Keine Angabe
Englisch
Analysis of thermal-protection systems for space-vehicle cryogenic-propellant tanks
Engineering Index Backfile | 1962
|Lightweight Thermal Protection Systems for Space Vehicle Propellant Tanks
SAE Technical Papers | 1964
|