Author : George R. Smolak
Publisher :
Page : 100 pages
File Size : 14,71 MB
Release : 1962
Category : Aeronautics
ISBN :
Book Description
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 state used for typical Mars missions.